УСТРОЙСТВО И СПОСОБ ЗАЩИТЫ ВЫЧИСЛИТЕЛЯ ТУРБОМАШИНЫ ЛЕТАТЕЛЬНОГО АППАРАТА ОТ ОШИБОК ИЗМЕРЕНИЯ СКОРОСТИ

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2015 122 453 A (51) МПК F01D 17/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015122453, 12.11.2013 (71) Заявитель(и): МИКРОТЮРБО (FR) Приоритет(ы): (30) Конвенционный приоритет: 13.11.2012 FR 1260802 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 15.06.2015 R U (43) Дата публикации заявки: 10.01.2017 Бюл. № 01 (72) Автор(ы): ПАСКЬЕ Людовик (FR), ЖОАШИМ Реми (FR) (86) Заявка PCT: (87) Публикация заявки PCT: WO 2014/076398 (22.05.2014) R U (54) УСТРОЙСТВО И СПОСОБ ЗАЩИТЫ ВЫЧИСЛИТЕЛЯ ТУРБОМАШИНЫ ЛЕТАТЕЛЬНОГО АППАРАТА ОТ ОШИБОК ИЗМЕРЕНИЯ СКОРОСТИ (57) Формула изобретения 1. Устройство защиты вычислителя турбомашины летательного аппарата от ошибок измерения скорости, содержащее: - в канале регулирования скорости (10): датчик скорости вала редуктора турбомашины (21), цепь измерения скорости (24), цепь регулирования скорости (26), - в канале контроля (11): датчик скорости вала газогенератора турбомашины(31), цепь измерения скорости (34), цепь управления остановом турбомашины (37), отличающееся тем, что: - оба датчика скорости (21, 31) являются двумя датчиками, которые обеспечены торцевыми зубьями двух фонических колес (20, 30) разных технологий и имеющие разное количество зубьев, - канал регулирования скорости (20) содержит цепь контроля скорости (25), которая выполняет сравнение частотного сигнала с минимальным порогом и которая выдает сигнал проблемы скорости (S1), когда измеряемая частота ниже, чем этот минимальный порог, - канал контроля (11) содержит цепь контроля скорости (35), которая выполняет Стр.: 1 A 2 0 1 5 1 2 2 4 5 3 A Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, стр. 3, ООО "Юридическая фирма Городисский и Партнеры" 2 0 1 5 1 2 2 4 5 3 FR 2013/052699 (12.11.2013) A 2 0 1 5 1 2 2 4 5 3 A R U 2 0 1 5 1 2 2 4 5 3 Стр.: 2 R U сравнение частотного сигнала с минимальным порогом и которая выдает сигнал проблемы скорости (S2), когда ...

Elektromagnetische Regelvorrichtung fuer Klein-Kraftmaschinen, insbesondere Klein-Dampfturbinen

VERWALTUNG UND OPTIMIERUNG VON LASTTEILUNG ZWISCHEN MEHREREN KOMPRESSORSTRÄNGEN ZUR STEUERUNG EINER HAUPTPROZESSGASVARIABLEN

Compressor e.g. exhaust gas turbocharger, rotation speed determining method for use in e.g. diesel internal combustion engine, involves obtaining rotation speed of compressor from periodic fluctuation of portion of pressure signal

The method involves directly detecting pressure in an area downstream of a compressor, and providing a corresponding pressure signal. The rotation speed of the compressor is obtained from the periodic fluctuation (u n) of a portion of the pressure signal. The periodic fluctuation is separated from the pressure signal through a high pass filtering, where a frequency of the periodic fluctuation is determined through a frequency analysis. The average value of the pressure signal is obtained through a low pass filtering. Independent claims are also included for the following: (1) a computer program for application in the method for determining rotation speed of a compressor (2) an electrical storage medium for a control and/or regulation device (3) a control and/or regulation device for an internal combustion engine (4) an internal combustion engine comprising a compressor.

Verfahren und Vorrichtung zum Regeln eines Dampfturbineneinlassstroms, um die Wärmebelastung für Gehäuseschale und Rotor zu begrenzen

In einem Verfahren zum Regeln eines Dampfstroms durch eine Dampfturbine, die einen Turbinenrotor aufweist, wird, basierend auf Berechnungen einer Wärmebelastung, in dem Turbinenrotor eine maximale Wärmeübertragungsrate (18) ermittelt. Eine maximale Dampfstromrate (20) lässt sich, basierend auf der maximalen Wärmeübertragungsrate, berechnen. Eine Ist-Dampfstromrate durch die Dampfturbine wird ermittelt, und ein Turbineneinlassventil (28) wird, basierend auf einer Differenz zwischen der Ist-Dampfstromrate und der maximalen Dampfstromrate, geregelt. Auf diese Weise lässt sich ein in die Dampfturbine eingespeister Dampfstrom geeignet regeln, so dass eine Wärmebelastung auf ein angemessenes Maß begrenzt wird, während Anlaufzeiten minimiert werden und die Betriebsbereitschaft optimiert wird.

Drehzahlregelsystem

An apparatus and method for detecting a damaged rotary machine aerofoil

Governor mechanism

Electronic speed sensor

High temperature speed or proximity sensor

Shaft break detection

Rotary speed governors

... 1,105,875. Fluid-pressure servomotor systems; centrifugal governors. DOWTY ROTOL Ltd. May 25, 1966 [April 13, 1965], No. 15755/65. Headings G3B and G3P. A speed governor comprises a rotating tubular member 12 enclosing a sleeve 13 which houses a spool valve 17 formed integral with a piston 30. A further sleeve 14, 15 has an orifice 40 the flow through which is controlled by a screw 48 carried in a member 42 supported by a leaf spring 43. Member 42 is counter balanced by a similar member 47 supported by a leaf spring 46. In use, pressurized fluid passes to orifice 40 via port 39 in sleeve 13, annular space 36, throttle 34 defined by spool valve 17 and sleeve 13 and passage 37, 38. If the speed increases above the set value, movement of member 42 lowers the pressure in chamber 38 and the spool valve moves to the left until the throttle 34 restores the pressure balance across piston 30. Such movement of the spool valve connects the left-hand side of motor M to a supply line 24 and the right ...

Improvements in or relating to devices responsive to rotational speed

... 762,507. Speed governors; engine stop-gear. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Jan. 3, 1955 [Jan. 7, 1954], No. 539/54. Classes 57 and 122 (4). [Also in Group XXXVII] A device responsive to rotational speed comprises a rotatable support 1, Fig. 2, a stably-deflected flexible strut 4 with its ends retained by the support, two weights 5 symmetrically attached to the strut and means for responding to a change in the stable deflection state of the strut occurring in operation at a predetermined speed as a result of the centrifugal action of the weights. When the predetermined speed is reached, the strut 4 suddenly takes up the position indicated by chain dotted line and strikes the head of a bolt 6 which slides in the casing 2 of the device against the resistance of a spring 7 so that a contacting collar 11 open-circuits a pair of terminals 10. The latter may be arranged to de-energize a solenoid 24, Fig. 5, which then releases an arm 25 and a butterfly valve 26 to rotate under the influence ...

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

OVERSPEED PROTECTION MECHANISM FOR TURBINES

MEASURING INSTRUMENT FOR THE COLLECTION OF A REVOLUTION IMPULSE OF AN ENGINE ROTOR AS WELL AS PROCEDURE FOR THIS

COVERED UP RAM AIR TURBINE GENERATOR SYSTEM AND ITS COOLING

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).

LOW DRAG DUCTED RAM AIR TURBINE GENERATOR AND COOLING SYSTEM

... ▓▓▓A low drag ducted ram air turbine generator and cooling system is provided. ▓The ducted ram air turbine generator and cooling system has reduced drag while ▓extracting dynamic energy from the air stream during the complete range of ▓intended flight operating regimes. A centerbody/valve tube (57) having an ▓aerodynamically shaped nose (76) is slidably received in a fairing (30) and ▓primary structure (50) to provide a variable inlet area. An internal nozzle ▓control mechanism (115) attached to the valve tube positions nozzle control ▓doors (70) to provide variable area nozzles directing air flow to the turbine ▓stator (80) and rotor blades (62) to maintain optimum generator efficiency.▓ ...

STEAM TURBINE CONTROLLER HAVING METHOD AND APPARATUS FOR PROVIDING VARIABLE FREQUENCY REGULATION

In a preferred embodiment, the invention relates to a steam turbine (10) having a speed-loop droop governor (32) with two load--frequency error gains (44, 46) (droops). The first gain (fast change) may be a conventional high gain (44) that is used for power loads that have a constant frequency. When using only the first gain, the high rate of the first gain causes the droop governor to shut off steam to the turbine if the speed of the turbine drifts above a narrow speed range centered on the rated speed set-point. The second gain 46 (slow change) is a low gain that causes the droop governor to tolerate a wide range of turbine speeds about the rated speed set-point (36).

DETERMINATION PROCESS FOR AIRCRAFT AIR SPEED AND AIRCRAFT EQUIPPED WITH IMPLEMENTATION MEANS

L'invention vise à fournir une information alternative de vitesse air d'un aéronef suffisamment précise et exploitable dans la partie du domaine de vol où des moyens basés sur la mesure de l'incidence ne sont pas adaptés. Pour ce faire, l'invention utilise des informations de pression délivrées par les moteurs de l'aéronef exploitables dans les systèmes au niveau avion de l'aéronef. En particulier, l'aéronef est équipé de moteurs (1) composé au moins d'une nacelle (30) et d'un attelage de compresseur/turbine (2, 3; 12, 14, 16, 18), l'aéronef comportant au moins une unité de traitement de données (40) et au moins un système au niveau avion. Au moins un moteur (1) de l'aéronef est muni d'au moins une sonde de pression statique de l'air ambiant (P1), sous la nacelle (30), de sondes de pression statique d'air (P2, P3) agencés au niveau moteur, d'une de sonde de pression (P4) en sortie de compresseur (12) d'au moins un capteur de vitesse de rotation (N1, N2), par exemple de soufflante (10), ...

APPARATUS FOR CONTROLLING A TURBO GENERATOR

The integral part of a power controller and of a PI speed controller is formed by a common integrator, both controllers always being engaged. With this linear interlinking of the two controllers, stability can be assured in the two limit cases of the network (rigid network and ohmic island) as well as practically in all cases in between.

GAS TURBINE SPEED DETECTION

A gas turbine engine having at least a rotor shaft operatively connecting a compressor apparatus and a turbine apparatus, comprises an auxiliary gear box and a phonic wheel apparatus. The auxiliary gear box is drivingly connected to the rotor shaft and the phonic wheel apparatus includes an oil pump having toothed gear and a sensor mounted to the oil pump for sensing a rotational speed of the toothed gear.

SYSTEM AND METHOD FOR DETECTING A SHAFT EVENT ON AN ENGINE

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

HIGH TEMPERATURE SPEED SENSOR

A gas turbine shaft speed sensor including a sensing coil comprised of a central conducting wire, the sensor and conducting wire is surrounded by a layer of mineral insulator and the mineral insulator is surrounded by a metallic, non magnetic, sheath. A sensing coil formed with this construction allows th e high operating temperatures and is robust.

CONTACTLESS CONNECTOR FOR USE IN A GAS TURBINE

The invention provides a system for monitoring an operational parameter of a gas turbine, including a magnetic coupling between a signal source and a data output terminal. The magnetic coupling comprises a primary coil electrically connected to the signal source and wound around a first magnetic core section, and a secondary coil electrically connected to the output terminal but electrically isolated from the primary coil and wound around a second magnetic core section, wherein the first and second magnetic core sections are physically separated from one another.

CONTROL PROCESS AND REGULATION SYSTEM FOR SUPPLYING COMPRESSED AIR TO A COMPRESSED AIR NETWORK, SPECIFICALLY IN AN AIRCRAFT

L'invention permet de s'affranchir des compresseurs de charge surdimensionnés pour fournir de l'air comprimé à un réseau pneumatique, en particulier au réseau d'un aéronef. Ce surdimensionnement absorbe les fortes pertes de charge générées par la régulation des vannes IGV d'accès d'air à ce compresseur. Pour palier ce problème, la gestion des variations des débits d'air prélevé est basée par une éjection régulée du surplus d'air non consommé par le réseau. Un système de fourniture d'air comprimé (1) à un réseau pneumatique (2) comporte un compresseur de charge (10), une alimentation en air (4) et un arbre de puissance (11) entraînant le compresseur de charge (10). Selon l'invention, il comporte également, en sortie d'air de ce compresseur de charge (10), un canal de liaison (6a) relié, d'une part, à un canal (6b) de connexion au réseau pneumatique (2) et, d'autre part, à un conduit d'évacuation d'air (6c) vers une tuyère d'échappement (34). Des vannes de prélèvement de débit d'air (12, ...

DEVICE AND METHOD FOR PROTECTING AN AIRCRAFT TURBOMACHINE COMPUTER AGAINST SPEED MEASUREMENT ERRORS

L'invention concerne un dispositif de protection d'un calculateur de turbo-machine d'aéronef contre les erreurs de mesure de vitesse comprenant : - sur un canal de régulation de vitesse (10) : un capteur de vitesse de l'arbre de la boite d'engrenage de la turbo-machine (21), un circuit de mesure de vitesse (24), et un circuit de régulation de vitesse (26), - sur un canal de surveillance (11) : un capteur de vitesse de l'arbre du générateur de gaz de la turbo-machine (31), un circuit de mesure de vitesse (34), et un circuit de commande de l'arrêt de la turbo-machine (37), dans lequel chaque canal (10, 11) utilise des caractéristiques dissimilaires aptes à éliminer les erreurs de modes communs, dans lequel chaque capteur de vitesse délivre un signal de fréquence pseudo-sinusoïdal et dans lequel ce dispositif comprend, sur chaque canal un circuit de surveillance de vitesse (25, 35) qui effectue une comparaison du signal de fréquence à un seuil minimum et qui délivre un signal d'erreur lorsque ...

Mechanisch-hydraulische Einrichtung zum Auslösen eines Impulses beim Unterschreiten einer Grenzdrehzahl eines umlaufenden Drehteiles

Einrichtung zur Erzeugung eines in seiner Grösse von der Drehzahl einer Welle abhängigen Flüssigkeitsdruckes

Regelungseinrichtung für drehzahlgeregelte Kraftmaschinen

Verfahren zur Drehzahlregelung mit Hilfsgrössenaufschaltung bei Maschinen, insbesondere Dampfturbinen

Regelanlage für eine Antriebsmaschine

Fluidbetriebenes Gerät zur Erzeugung eines dem Produkt zweier Grössen entsprechenden Signals

Vorrichtung zum Erfassen des Unterschreitens einer bestimmten Drehzahl einer Welle

Starter control device to be associated with speed regulators for main turbines

Methods and systems for monitoring the performance of rotor blades.

Die Erfindung betrifft ein System und ein Verfahren zur Überwachung der Funktionstüchtigkeit eines Rotors. Das System enthält ein Verarbeitungssubsystem, das mehrere Frequenzspitzenwerte, die zwei oder mehreren jeweiligen Signalfenstern entsprechen, durch iteratives Verschieben der zwei oder mehreren Signalfenster entlang von Delta-Ankunftszeitsignalen (206), die einer Laufschaufel in dem Rotor entsprechen, generiert, einen oder mehrere Resonanzfrequenz-Rotordrehzahlbereiche der Laufschaufel durch Identifizierung von Rotordrehzahlen, die einem Teilsatz der mehreren Frequenzspitzenwerte entsprechen, bestimmt (214) und die Laufschaufel überwacht, um eines oder mehrere Defekte in der Laufschaufel während der Resonanzfrequenz-Rotordrehzahlbereiche festzustellen.

Methods and systems for monitoring the performance of rotor blades.

Die Erfindung betrifft ein System und ein Verfahren zur Überwachung der Funktionstüchtigkeit eines Rotors. Das System enthält ein Verarbeitungssubsystem, das mehrere Frequenzspitzenwerte, die zwei oder mehreren jeweiligen Signalfenstern entsprechen, durch iteratives Verschieben der zwei oder mehreren Signalfenster entlang von Delta-Ankunftszeitsignalen (206), die einer Laufschaufel in dem Rotor entsprechen, generiert, einen oder mehrere Resonanzfrequenz-Rotordrehzahlbereiche der Laufschaufel durch Identifizierung von Rotordrehzahlen, die einem Teilsatz der mehreren Frequenzspitzenwerte entsprechen, bestimmt (214) und die Laufschaufel überwacht, um eines oder mehrere Defekte in der Laufschaufel während der Resonanzfrequenz-Rotordrehzahlbereiche festzustellen.

Compressed air-driven tool.

Druckluftgetriebenes Werkzeug mit einem elektromagnetisch betätigten Steuerglied (27) zur Steuerung eines pneumatischen Steuerkreises zur Aufrechterhaltung eines lastunabhängigen Drehmoments bei konstanter Drehzahl. Das Werkzeug umfasst ein Hauptventil (5) und einen Generator (43), der auf der Welle (49) eines Turbinenrads (51) sitzen kann. Mit einem Drehzahlsensor (75) wird die Drehzahl der Welle (49) gemessen und bei Drehzahlabfall infolge einer Last wird der Zufluss von Druckluft an das Hauptventil (5) gesteuert.

Compressed air-driven tool.

Druckluftgetriebenes Werkzeug mit einem elektromagnetisch betätigten Steuerglied (27) zur Steuerung eines pneumatischen Steuerkreises zur Aufrechterhaltung eines lastunabhängigen Drehmoments bei konstanter Drehzahl. Das Werkzeug umfasst ein Hauptventil (5), welches in einem Antriebsgehäuse (1) von der zugeführten Druckluft gegen die Kraft einer Schraubenfeder (13) verschiebbar angeordnet ist und einen Generator (43), der auf der Welle (49) eines Turbinenrads (51) sitzt. Mit einem Drehzahlsensor (75) wird die Drehzahl der Welle (49) gemessen und bei Drehzahlabfall infolge einer Last wird der Zufluss von Druckluft an das Hauptventil (5) gesteuert.

Improvements with the mechanisms of distribution by valves

DEVICE TO DETECT a DIFFERENCE BETWEEN the NUMBER OF REVOLUTIONS OF TWO ROTATING SHAFTS AND APPLICATION HAS a MEASUREMENT OR HAS an ORDERING Of CONTROL

Dispositif et procédé de contrôle de la survitesse d'un moteur à turbine à gaz

L'invention concerne un dispositif 70 de commande pour moteur à turbine à gaz 12 comportant une turbine 50, qui reçoit un signal représentatif d'une survitesse de celle-ci et réduit le courant d'air entrant dans la turbine en réponse au signal de survitesse de la turbine. L'invention comprend également un dispositif de commande pour moteur à turbine à gaz ayant une aube directrice variable 32, une turbine 50 et un orifice placé 32 en amont de la turbine qui permet à l'air de sortir du moteur. Le dispositif reçoit un signal représentatif d'une survitesse de la turbine et produit un signal de réglage d'orifice afin d'ajuster l'orifice de façon que l'air sorte du moteur en réponse au signal de survitesse de la turbine. L'invention concerne en outre un procédé pour commander un moteur à turbine à gaz ayant une aube directrice variable, une turbine et un orifice placé en amont de la turbine, comportant les étapes consistant à recevoir un signal représentatif d'une survitesse de la turbine et ...

Speed sensor apparatus

SENSOR DEVICE FOR THE CONTACTLESS DETECTION OF A ROTATION PROPERTY OF A ROTATABLE OBJECT

The invention relates to a sensor device (10) for the contactless detection of a rotatable object (12), in particular for the detection of the rotational speed of a compressor wheel (14) of a turbo charger (18). The sensor device (10) comprises a sensor housing (22). The sensor device (10) also comprises at least one magnetic field generator (26) for generating a magnetic field at the location of the rotatable object (12) and at least one magnetic field sensor (28) for detecting a magnetic field generated by turbulent flows of the rotatable object (12). The sensor device (10) is further provided with at least one connection element (58, 60, 62), wherein the connection element (41, 58, 60, 62) is configured to connect the sensor device (10) to a device (40) that comprises the rotatable object (12), in particular a turbo charger (18) in such a manner that the magnetic field generator (26) and the magnetic field sensor (28) are at least in part jointly arranged in a sensor segment (24) of ...

TURBINE ENGINE WITH A ROTOR SPEED SENSOR AND CORRESPONDING OPERATING METHOD

A turbine engine includes at least one rate sensor mounted adjacent a fan rotor assembly. The sensor measures a rate of rotation of the fan rotor assembly by detecting the temporary proximity of a portion of the fan rotor assembly during rotation. In one embodiment, the sensor detects the proximity of at least one of a plurality of fan blades to determine the rate of rotation of the fan rotor assembly. In another embodiment, the sensor detects the proximity of at least one of a plurality of turbine blades mounted to the fan rotor assembly. The sensor may be an electromagnetic sensor that detects the proximity of ferromagnetic portions of the fan rotor assembly, such as the fan blades or the turbine blades.

Signal processing method and apparatus

A method for generating a series of output signals represented by a series of measurement signals which is particularly useful in the compensation for jatter, missing spurious pulses or plates when applied to the processing of signals from a speed probe monitoring the speed of a rotating bladed shaft. The method includes the steps of predicting a value for a first measurement signal from a historical measurement signal value, generating a first output signal from the predicted value of the first measurement signal; comparing the measurement signal to its predicted value, and: if the measurement signal is within a pre-determined range of acceptable values, using the first measurement signal to predict a value for a second measurement signal; if the measurement signal is outside the pre-determined range of acceptable values, using the first predicted value to predict a second measurement signal, and generating a second output signal from the predicted value of the second measurement signal ...

GAS TURBINE ENGINE VANE EMBEDDED BEAM INTERRUPT OPTICAL TIP-TIMING PROBE SYSTEM

A method of observing an airflow passage within a gas turbine engine includes locating a support in view of an airflow passage and housing an optical fiber within the support.

ELEMENT WHICH GENERATES A MAGNETIC FIELD

MANAGEMENT AND OPTIMIZATION OF LOAD SHARING BETWEEN MULTIPLE COMPRESSOR TRAINS FOR CONTROLLING A MAIN PROCESS GAS VARIABLE

BLADE ANGLE FEEDBACK DEVICE WITH VARIABLE MAGNETIC PERMEABILITY

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 ДЛЯ ОПРЕДЕЛЕНИЯ ЧАСТОТЫ ВРАЩЕНИЯ ВРАЩАЮЩЕЙСЯ ДЕТАЛИ МАШИНЫ С ИЗБЫТОЧНЫМИ ДАТЧИКАМИ И СХЕМАМИ ОЦЕНКИ

... 1. Устройство для контроля частоты вращения вращающейся детали (3) машины, отличающееся тем, что предусмотрены два параллельно расположенных частичных устройства (5, 7), причем каждое частичное устройство (5, 7) содержит, по меньшей мере, три сигнальных входа (51, 71), к которым является соответственно подводимым выходной сигнал (11) датчика (9) частоты вращения, вычислительный блок (53, 73), посредством которого, по меньшей мере, одним из выходных сигналов (11) одного из датчиков (9) частоты вращения (9) является вычисляемая, по меньшей мере, частота вращения вращающейся детали (3) машины, и, по меньшей мере, один сигнальный выход для выдачи вычисленной вычислительным блоком частоты вращения, и причем соответствующие друг другу сигнальные входы (51, 71) частичных устройств (5, 7) параллельно нагружены выходным сигналом (11) одного из датчиков частоты вращения. 2. Устройство по п.1, отличающееся тем, что каждое частичное устройство (5, 7) содержит, по меньшей мере, два сигнальных выхода ...

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 ...

Regler-Schaltung für einen Dampfkraftwerksblock

Mechanisch-hydraulische Einrichtung zum Ausloesen eines Impulses beim Unterschreiten einer Grenzdrehzahl eines umlaufenden Drehteiles

Method for managing a breakdown of a turbine engine starter valve

Improvements in or relating to electric ignition starting devices for gas turbine engines

... 701,659. Gas turbine plant. SOC. D'ETUDES DE CARBURATION POUR L'AUTOMOBILE ET L'AVIATION S.E.C.A.A. Oct. 10, 1951 [Oct. 11, 1950], No.23608/51. Class 110 (3). [Also in Group XXVII] A gas turbine engine has means responsive to the engine speed for closing a switch in the ignition circuit when a predetermined speed which is equal to or greater than the self running speed, is reached. The circuit 2 of the electric ignition device 3 includes a main switch 4 and a speed-operated switch 5. The switch 5 is operated by the sleeve 11 of a governor 6 driven by the engine or the starter motor when the predetermined speed is reached. An electromagnetically operated auxiliary fuel injector 9 may be arranged in parallel with the ignition device 3. Modifications in which the main switch 4 is used, to energize an electric starter motor or to energize the ignition of an internal combustion reciprocating engine starter motor are described. If the starter motor includes magneto ignition, this magneto may ...

Shaft break detection

SELF-CHECKING SPEED GOVERNOR ARRANGEMENT

Isothermal de-iced sensor

Contactless connector for use in a gas turbine

A system for monitoring an operational parameter of a gas turbine, including a magnetic coupling between a signal source and a data output terminal. The magnetic coupling comprises a primary coil 57 electrically connected to the signal source 54, and a secondary coil 59 electrically connected to the output terminal but electrically isolated from the primary coil. The primary and secondary coils may be wound around separate magnetic cores 58,60 which are physically separated from one another, perhaps by an air gap. Alternatively, the coils may be wound around the same core with the secondary coil arranged to be detachable from the core.

Shaft monitoring system

SPEED MONITORING ARRANGEMENT

... 1439395 Valves SIEMENS AG 5 Nov 1973 [6 Nov 1972] 51335/73 Heading F2V [Also in Divisions Gl H2 and F1] Three hydraulic valves 23, 24, 25 are connected in parallel in an oil circuit H01, each of the valves being controlled by a respective pair of electromagnetic valves 20a, 20b, 21a, 21b, 22a, 22b. Each of the control valves, in the "on" condition sends auxiliary control oil St0 through a non-return valve 66 to the respective spring-loaded valve 23, 24, 25 so that the return flow path RF for the oil from H01 is shut off. When either one of the two control valves, associated with an hydraulic valve, closes, e.g. 20a or 20b the control oil pressure of the other control valve acts on the non-return valve 66 to shut off the one valve whereby the associated hydraulic valve remains closed. Only if both the electromagnetic control valves are deenergized is the corresponding hydraulic valve changed over by oil pressure and spring force so as to connect oil circuit H01 with the return path RF. The ...

SELF-CHECKING SPEED GOVERNOR ARRANGEMENT

Fluid operated prime mover

... 848,526. Centrifugal governors. ROTOL Ltd. April 3, 1959 [April 11, 1958], No. 11650/58. Class 57. The centrifugally operated valve for controlling the flow of fluid through a prime mover (such as a turbine or swash-plate motor) having a motor-driven shaft 4 comprises two relatively movable members 6, 23 rotatable with the shaft and having ports 21, 22, 24 which co-operate with inlet and outlet galleries 11, 14 in the valve housing 2 and centrifugal control means arranged to produce relative rotation of the members 6, 23 so as to control the rate of fluid flow. As shown applied to a compressed air turbine, the valve member 23 is coupled to the shaft 4 by a torsion spring 25 connected at one end 30 to a threaded sleeve 31 screwed to the end of the shaft and at the other end 26 to the valve member. The latter member is provided with two abutments 56, 57, Fig. 3, which engage with bearings 50, 51 carried by flywieghts 40, 41 pivotally mounted in the rotor 5 of the turbine; the loading of the ...

OVERSPEED PROTECTION MECHANISM FOR TURBINES

HEATING AND CALCINING OF POWDER AND/OR PULVERIZED MATERIALS

EDDY CURRENT SENSORS

An inductive eddy current sensor, for use for example for measuring the speed of a turbine by detecting the passage of turbine blades (21) past a probe incorporating the sensor, includes a magnet (23) positioned so that the blades (21) pass through the flux pattern generated by the magnet (23). At least one pick-up coil (28) devoid of a core of soil magnetic is positioned alongside the magnet to pick up signals generated by eddy currents generated in the turbine blades as they cut through the flux pattern, without thereby altering the flux pattern. In a modified arrangement, the pick up coil surrounds the magnet, again without affecting the flux pattern.

TURBINE SPEED CONTROL

REGULATION SYSTEM FOR DOUBLE-SHAFT GAS TURBINES

... "REGULATION SYSTEM FOR DOUBLE-SHAFT GAS TURBINES" A regulating system for regulating a double-shaft gas turbine, wherein simultaneously: the fuel feed electrovalve is governed by a signal proportional to the difference beetween the number of revolutions per minute of the power turbine and a reference value; the movable nozzles of the power turbine are governed by a signal ether proportional to the difference between the number of revolutions per minute of the compressor and a reference value; or proportional to the difference between the temperature of the exhaust gases and a relevant reference value; and the movable stator-blades of the compressor are governed by a signal proportional to the ratio between the revolutions per minute of the compressor to the square root of the ratio of the absolute ambient temperature to an absolute reference or design temperature.

OPERATION OF AIRCRAFT ENGINES DURING TRANSIENT CONDITIONS

Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system.

Method for determining the air speed of an aircraft and aircraft provided with a means for implementing same

The invention relates to a method for determining the air speed of an aircraft and aircraft provided with a means for implementing same. The invention aims to provide the accurate enough and feasible aircraft optional airspeed information recording in part of airdromes not suitable for correlated measurement means, so that the invention utilizes the pressure information supplied by an aircraft engine below the aircraft height of the aircraft and feasible in a system. The aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system below the engine level. At least one engine of the aircraft is equipped with at least one ambient static pressure probe for measuring the ambient air under the pod, also, air static pressure probes arranged at the engine levels, a pressure probe at the output end of the compressor, at least one rotation speed sensor, for example of a blower, and ...

PROCEDE POUR ETABLIR UNE VALIDITE DE SYNTHESE ENTRE DEUX SOURCES DE SIGNAUX, APPLICABLE NOTAMMENT A LA COMMANDE DE MOTEURS A TURBINE

LA PRESENTE INVENTION CONCERNE DES CONTROLES CROISES ET LA SYNTHESE DE SIGNAUX REPRESENTANT DES PARAMETRES, PLUS PARTICULIEREMENT POUR UNE APPLICATION AUX MOTEURS A TURBINE. CE PROCEDE EST CARACTERISE EN CE QUE L'ON PRODUIT UN PREMIER SIGNAL N1 INDIQUANT UN PREMIER PARAMETRE DETECTE, EN REPONSE A CELUI-CI, ON PRODUIT UN SECOND SIGNAL N2 INDIQUANT UN SECOND PARAMETRE LIE AU PREMIER PARAMETRE, EN REPONSE A CE SECOND PARAMETRE, ON SURVEILLE LA VERACITE DU PREMIER SIGNAL ET DU SECOND SIGNAL, ON PRODUIT UN PREMIER SIGNAL SYNTHETISE N1SYNTH SI LA VERACITE DU PREMIER SIGNAL EST INFERIEURE A LA VERACITE DU SECOND SIGNAL ET ON PRODUIT UN SECOND SIGNAL SYNTHETISE N2SYNTH SI LA VERACITE DU PREMIER SIGNAL EST AU MOINS EGALE A LA VERACITE DU SECOND SIGNAL.

PERFECTIONNEMENT AUX SYSTEMES DE REGULATION DE VITESSE DES MOTEURS HYDRAULIQUES OU THERMIQUES

DISPOSITIF DE CONTROLE DE DEMARRAGE PAR ADJONCTION D'UNE REGULATION DE VITESSE POUR TURBOMOTEUR CARACTERISE PAR LE FAIT QU'IL COMPREND UN CIRCUIT A BOUCLE DE FERMETURE POUR ASSURER LE CONTROLE DE L'ACCELERATION DURANT TOUTE LA PHASE DE MONTEE DE LA VITESSEDE ROTATION, AYANT COMME REFERENCE D'ACCELERATION LE NIVEAU MAXIMUM QUI SORT D'UN CIRCUIT AYANT EN ENTREE LE SIGNAL D'ERREUR ENTRE LA VALEUR DE LA VITESSE ACTUELLE DU GROUPE A CONTROLER ET UNE VALEUR DE REFERENCE REPRESENTANT LA VITESSE A ATTEINDRE, DE FACON QUE, QUAND CETTE ERREUR DEVIENT INFERIEURE AU NIVEAU INDIQUE, AU CONTROLE DE L'ACCELERATION S'AJOUTE AUTOMATIQUEMENT UN CONTROLE DE LA VITESSE NECESSAIRE POUR LA REGULATION DE LA VITESSE A UNE VALEUR PREDETERMINEE.

METHOD AND SYSTEM FOR DETECTING THE ANGULAR POSITION OF THE BLADES OF A ROTOR OF A TURBOMACHINE

SONDE A CAPTEUR MAGNETIQUE, NOTAMMENT POUR MESURER LA VITESSE ANGULAIRE DE L'ARBRE DU COMPRESSEUR D'UN TURBOREACTEUR

L'invention concerne une sonde destinée, au moyen d'un capteur magnétique, à mesurer la vitesse de rotation d un arbre Le capteur est relié de façon étanche à la tige de la sonde au moyen d'un soufflet et d'un ressort qui autorisent un certain déplacement axial de l'un par rapport à l'autre. Application aux techniques de télémesure, notamment de la vitesse de rotation de l'arbre du compresseur d'un turboréacteur.

PROBE HAS EMISSION OF SIGNAL FOR DEVICE OF DETECTION SPEED OF TURBINE

Testing the air gap of a rotation sensor to prevent damage to the sensor

METHOD AND DEVICE FOR MEASURING THE FLOW RATE OF COOLING AIR FROM A TURBINE ENGINE CASING

SYSTEM Of ANALYSIS SPEED FOR CONTROL DEVICE OF TURBINE

EXHAUST-GAS TURBOCHARGER

VIRTUAL TURBINE SPEED SENSOR

According to one exemplary embodiment, a virtual turbine speed sensor for a multi-stage turbocharger system (180) is disclosed. The multi-stage turbocharger system includes at least two sequential turbochargers (181, 182) each having a compressor (184, 186) and a turbine (183, 185). The virtual turbine speed sensor includes a compressor efficiency module (220) configured to estimate an efficiency of a first compressor of the at least two turbochargers, an inter-stage air temperature module (230) configured to estimate an inter-stage temperature of air between the at least two compressors, and a turbine speed module (240) configured to estimate a speed of a second turbine of the at least two turbochargers. The inter-stage temperature estimate of air is based at least partially on the efficiency of the first compressor and the speed estimate of the second turbine is based at least partially on the inter-stage air temperature estimate.

ELEMENT WHICH GENERATES A MAGNETIC FIELD

The invention relates to an element which generates a magnetic field for fastening a compressor wheel to a turboshaft of an exhaust-gas turbocharger, having a basic body and a thread. In order to specify an element which generates a magnetic field for fastening a compressor wheel to a turboshaft, which element generates as high a magnetic field strength as possible and nevertheless can absorb without damage the forces and the tightening torques which occur during fastening of the compressor wheel to the turboshaft, the entire basic body comprises a magnetic material and a sleeve is arranged in the basic body, which sleeve comprises a non-magnetic material and has the thread which can be screwed to a mating thread of the turboshaft.

METHOD FOR MONITORING A TURBOSHAFT ROTATIONAL SPEED

The invention relates to a method for monitoring the speed of rotation of a turboshaft which rotatably mounted in a turbocharger, wherein a magnetic field-modifying element is arranged on the turboshaft and generates the variation of the magnetic field proportionally to the speed of rotation of the turboshaft and a sensor for detecting the variation of the magnetic field and converting it into the speed of rotation electronic signal is provided. The aim of said invention is to develop a method for controlling the speed of rotation of a turboshaft which makes it possible to reliably protect the turbocharger against a damage produced by the speed of rotation exceeding an admissible upper limit. For this purpose, in order to detect a faulty rotational speed signal, the pulse duty factor thereof is evaluated and, in the case of a faulty rotational speed signal, the speed of rotation of the turboshaft is reduced in such a way that the destruction of the turbocharger by the exceeding rotational ...

PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface.

SYSTEM AND METHOD FOR MEASURING AN AXIAL POSITION OF A ROTATING COMPONENT OF AN ENGINE

Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor coupled to the rotating component, the rotating component having a plurality of position markers distributed about a surface thereof, the position markers having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.

Method of using a turbine overspeed trip testing system

A turbine overspeed trip test data system is a portable system by which an operator can electronically gather and log data during a turbine overspeed test. A plurality of sensors can be affixed to various components of the turbine for gathering test data to be received by a processing unit to assess the operation of the turbine overspeed trip protection components. The test data may be compiled into a turbine test log. A method for processing the gathered sensor data is also provided.

Method of operating a compressor near the compressor pumping limit and compressor

In a method of operating a compressor near the compressor pumping limit wherein the compressor includes a control arrangement for adjusting the momentary operating state of the compressor, the flow velocity of a mass flow through the compressor in the boundary layer along the wall of the flow passage is determined for detecting operation of the compressor close to the pumping limit from a reversal of the direction of the mass flow vector in the boundary layer and the control arrangement is actuated so as to prevent the compressor from transgressing the pumping limit.

APPARATUS FOR HEATING AND CALCINING OF POWDER AND/OR PULVERIZED MATERIALS

An apparatus for preheating or calcining of powder and/or pulverized materials in which a cylindrical combustion furnace comprises a precombustion chamber and a main combustion chamber. Air inlet pipes are connected tangentially to said respective chambers in order that the air for use in combusting blown in said chambers from said air inlet pipes does a circling movement of the air stream.

CONTROL DEVICE FOR SUPERCHARGER IN AUTOMOBILE ENGINE

PURPOSE: To hold durability of a device further correctly perform its operation, by controlling a flow in a bypass circuit through an actuator with a control signal of a control unit from an optically detected signal of turbine speed. CONSTITUTION: A compressor 9 is driven by a turbine 8 to generate supercharge pressure. Its rotary motion is converted into a rotary speed in such a manner that incident light of an emitting unit 17 through an optical fiber 15 from an LED is received by a light receiving unit 18 through a hole 25 in a shaft 10 to enter a control unit ECU via an optical fiber 19 and O/E converter. The ECU feeds a control signal to a step motor actuator 20 and control a bypass valve 21 in such a manner as to obtain a preset speed. In this way, rotation is detected at a side of the compressor 9, and prescribed rotary motion can be performed without being relatively affected by an easily changing flow of exhaust gas. COPYRIGHT: (C)1983,JPO&Japio ...

УСТРОЙСТВО ГЕНЕРАЦИИ СОЛНЕЧНОЙ ЭНЕРГИИ И ВНЕШНИЙ ПАРОВОЙ ИСТОЧНИК ДОПОЛНИТЕЛЬНОЙ ЭЛЕКТРОЭНЕРГИИ

FIELD: energy. SUBSTANCE: invention relates to electric energy generation system using ecologically clean energy-solar and external steam hybrid electric energy generation system. System comprises solar steam generator outlet end of which is connected to inlet (3) of high pressure steam of turbine (2) through first control valve (18), steam outlet end of external controller (15) of steam is connected to inlet (3) of high pressure steam of turbine (2) through second control valve (20) and second switching valve (19), outlet (4) of low pressure steam turbine unit (2) is connected to inlet end of condensation device (5), while its outlet end is connected to inlet end of deaerator (6), its outlet end is connected to inlet end of pump (7) for supply of water, its outlet end is connected to inlet end of return water of solar steam generator through first switching valve (16), and the outlet end of pump (7) is additionally connected with bypass (11) of return water of external steam through fourth switching valve (23). System further includes tank (9) for storage of soft water. EFFECT: invention enables using waste heat of industrial production for elimination of dependence on weather and unstable and intermittent concentration of heat solar radiation. 6 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 602 708 C2 (51) МПК H02S 10/00 (2014.01) F01K 11/02 (2006.01) F03G 6/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2015109761/06, 18.10.2012 (24) Дата начала отсчета срока действия патента: 18.10.2012 Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): ЧЭНЬ Илун (CN), ЯН Цинпин (CN), ЧЖАН Яньфын (CN) 12.12.2011 CN 201110411979.8; 12.12.2011 CN 201120515674.7 R U (73) Патентообладатель(и): УХАНЬ КАЙДИ ИНДЖИНИРИНГ ТЕКНОЛОДЖИ РИСЕРЧ ИНСТИТЬЮТ КО., ЛТД. (CN) (43) Дата публикации заявки: 10.10.2016 Бюл. № 28 (56) Список документов, цитированных в отчете о поиске: CN 201827035 U, 11.05.2011 ;CN ...

УСТРОЙСТВО ДЛЯ ОПРЕДЕЛЕНИЯ ЧАСТОТЫ ВРАЩЕНИЯ ВРАЩАЮЩЕЙСЯ ДЕТАЛИ МАШИНЫ

FIELD: the invention refers to measuring technique and may be used in systems of controlling of turning speed for example of the working shaft of a turbine. SUBSTANCE: the arrangement has at least one signal input to which an output signal of the sensor of the turning frequency is attached and also a calculating block through which the output signal of the sensor of the turning frequency forms actual meanings of the turning frequency of the rotating detail of the car. At that through the first out of at least two signal outputs only such actual turning frequencies are formed whose values are contained in the given range of the turning frequency which is a true subset of real working range of the turning frequency of the rotating detail of the car. EFFECT: expands functional possibilities. 18 cl, 2 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2 313 099 (13) C2 (51) ÌÏÊ G01P 1/00 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2005102713/28, 30.06.2003 (72) Àâòîð(û): ÀÐÅÑÒÎÂÀ Ëþäìèëà (RU), ÕÀÍÑ Êàðë (DE), ÃÀËÊÈÍ Èãîðü (RU), ÐßÇÀÍΠÑåðãåé (RU) (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 30.06.2003 (43) Äàòà ïóáëèêàöèè çà âêè: 27.10.2005 (45) Îïóáëèêîâàíî: 20.12.2007 Áþë. ¹ 35 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: RU 2082016 C1, 20.06.1997. JP 59039907 A, 05.03.1984. US 4035624 A, 12.07.1977. RU 2094354 C1, 27.10.1997. SU 1737344 A1, 30.05.1992. DE 19545520 A, 13.06.1996. RU 1517489 C1, 20.07.1998. RU 2128879 C1, 10.04.1999. (86) Çà âêà PCT: DE 03/02171 (30.06.2003) C 2 C 2 (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 04.02.2005 R U 2 3 1 3 0 9 9 (87) Ïóáëèêàöè PCT: WO 2004/005939 (15.01.2004) Àäðåñ äë ïåðåïèñêè: 103735, Ìîñêâà, óë. Èëüèíêà, 5/2, ÎÎÎ "Ñîþçïàòåíò", ïàò.ïîâ. Î.Ô.Èâàíîâîé (54) ÓÑÒÐÎÉÑÒÂÎ ÄËß ÎÏÐÅÄÅËÅÍÈß ×ÀÑÒÎÒÛ ÂÐÀÙÅÍÈß ÂÐÀÙÀÞÙÅÉÑß ÄÅÒÀËÈ ÌÀØÈÍÛ (57) Ðåôåðàò: Èçîáðåòåíèå îòíîñèòñ ê èçìåðèòåëüíîé òåõíèêå è ìîæåò áûòü èñïîëüçîâàíî â ...

Speed sensor authority for and method of measuring speed of rotation

Sensor arrangement for measuring a rotation speed of a salient member of a rotatable body comprising a first electrode arrangement providing a first input, a second electrode arrangement providing a second input different from the first input, the first and second electrode arrangements configured so noise in the first and second inputs is substantially the same, and wherein variations in the first and second inputs are caused by rotation of the rotatable body and the salient member past the first and second electrode arrangements, an output arrangement for receiving the first and second inputs, and for providing an output proportional to a difference between the first and second inputs, and a retaining member for retaining one or more of the first and second electrode arrangements and output arrangement, the speed of rotation of the salient member measurable from a variation in the output caused by rotation of that salient member.

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 for measuring the deformation of a turbo-machine blade during operation of the turbo-machine

A method for measuring the deformation of a turbo-machine blade including: a step of positioning at least one accelerometer onto a local point of the turbo-machine blade; a first step of measuring the centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the given measurement direction at a first predetermined speed; a second step of measuring the centrifugal, at a second predetermined speed; a step of determining the angular displacement of the measurement direction of the accelerometer relative to the centrifugal direction as a function of the first acceleration measurement and the second acceleration measurement, said angular displacement corresponding to an angular deformation of the local point of the turbo-machine blade.

Fan Axial Containment System

A gas turbine engine () and method for containing a fan inside an engine after a fan thrust bearing assembly failure. The engine () may comprise a fan (), a housing () including a compartment (), a fan shaft () inside the compartment () and comprising a bowl (), a support structure () inside the compartment (), a speed sensor pickup () mounted on the outer surface () of the bowl (), a speed sensor () mounted on the support structure (), and a fan thrust bearing assembly () disposed forward of the bowl (). The fan thrust bearing assembly () including a bearing (). The speed sensor () and the sensor pickup () define a defining a sensor gap (). The bearing () and the outer surface () defining a fan thrust bearing gap (), wherein the sensor gap () is less than the fan thrust bearing gap. 1. A gas turbine engine disposed about a longitudinal engine axis (A) , the engine comprising:a fan;an exterior housing including an interior compartment disposed adjacent to the fan;a fan shaft disposed inside the compartment, the fan shaft configured to drive the fan, the fan shaft comprising an elongated pole and a bowl, the bowl including an outer surface and an inner surface;a fan bearing support structure disposed inside the compartment;a speed sensor pickup mounted on the outer surface of the bowl;a speed sensor mounted on the fan bearing support structure, the speed sensor and the sensor pickup defining a sensor gap in the axial direction; anda fan thrust bearing assembly disposed forward of the bowl, the fan thrust bearing assembly including a bearing, the bearing and the outer surface of the bowl defining in the axial direction a fan thrust bearing gap, wherein the sensor gap is less than the fan thrust bearing gap.2. The gas turbine engine of claim 1 , in which the fan thrust bearing assembly includes mounting hardware claim 1 , wherein the fan thrust bearing assembly is disposed adjacent to the pole and is mounted below the speed sensor to the fan bearing support structure ...

POWER DETERMINATION METHOD AND TURBOMACHINE

A method determines a power of a turbomachine which has, in the interior thereof, a turbine housing which is supported with respect to a torque. The method includes current bearing forces of the turbine housing that are first of all determined and differences from stored permanent bearing forces that are then formed. The torque is then determined as the sum of these differences and the power of the turbomachine is determined therefrom. 1. A method for determining a power of a turbomachine which , in its interior , has a turbine housing which is supported with respect to a torque , the method comprising:determining present load-bearing forces of the turbine housing,calculating differences with respect to stored permanent load-bearing forces,determining the torque as a sum of said differences, anddetermining the power of the turbomachine from said torque.2. The method as claimed in claim 1 , further comprisingdetermining an elastic deformation of carrier elements of the turbine housing,wherein the present load-bearing forces are determined in each case from the elastic deformation of the carrier elements.3. The method as claimed in claim 2 , further comprisingdetermining a relationship between the deformation of the carrier elements and the present load-bearing forces through the application of a predefined force.4. The method as claimed in claim 3 , further comprisinggenerating the predefined force by an application of a known negative pressure in the interior of the turbomachine in combination with the interior being sealed with respect to the surroundings.5. A turbomachine comprising:a turbine housing which is arranged in an interior of the turbomachine,wherein the turbine housing has a central axis and multiple carrier elements arranged spaced apart from the central axis, by means of which carrier elements the turbine housing is supported with respect to a torque acting about the central axis,wherein each carrier element is assigned a sensor for determining a ...

RAW MATERIAL GAS LIQUEFYING DEVICE AND METHOD OF CONTROLLING THIS RAW MATERIAL GAS LIQUEFYING DEVICE

A raw material gas liquefying device includes a feed line which feeds a raw material gas, a refrigerant circulation line which circulates a refrigerant, the refrigerant circulation line including an expansion unit of a turbine type which expands the refrigerant to generate cryogenic energy, and an expansion unit entrance valve provided at an entrance side of the expansion unit, a heat exchanger which exchanges heat between the raw material gas and the refrigerant, a cooler which performs initial cooling of the raw material gas and the refrigerant by heat exchange with liquid nitrogen, and a controller which manipulates the opening rate of the expansion unit entrance value and performs a feedback control so that the rotation speed of the expansion unit reaches a predetermined target value, and outputs the opening rate command to the expansion unit entrance valve, at start-up and stop of the expansion unit. 1. raw material gas liquefying device comprising:a feed line which feeds a raw material gas whose boiling temperature is lower than a boiling temperature of nitrogen;a refrigerant circulation line which circulates a refrigerant for cooling the raw material gas, the refrigerant circulation line including an expansion unit of a turbine type which expands the refrigerant to generate cryogenic energy, and an expansion unit entrance valve provided at an entrance side of the expansion unit;a heat exchanger which exchanges heat between the raw material gas and the refrigerant;a cooler which performs initial cooling of the raw material gas and the refrigerant by heat exchange with liquid nitrogen;an expansion unit rotation speed sensor which detects a rotation speed of the expansion unit; anda controller which generates an opening rate command for the expansion unit entrance valve by performing a feedback control so that the rotation speed of the expansion unit reaches a predetermined target value, and outputs the opening rate command to the expansion unit entrance valve, ...

Method and system for detecting damage to the mobile blades of an aircraft

A method for detecting damage to one or more mobile blades of an impeller of an aircraft engine, includes measuring the speed of the engine, and for each blade acquiring, by a plurality of sensors, measurements of blade-tip passage times; calculating for each sensor, a deflection of the blade tip; extracting a dynamic component of deflection for each of the calculated deflections; detecting the number of functioning sensors; selecting the dynamic components to be processed based on the detecting step; determining, for at least one blade, a variation of the dynamic behavior of the blade for each functioning sensor; and, for each blade for which a variation of the dynamic behavior has been determined, identification of potential damage to the blade.

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.

METHOD AND APPARATUS FOR MONITORING THE OPERATION OF A POWER GENERATING INSTALLATION

A method for monitoring operation of a power generating installation that has at least one generator that is driven by a rotating machine, in which values of an operating parameter of the generator and/or rotating machine are captured and stored, it is ascertained whether the value of the operating parameter at prescribed checking times lies outside an admissible range, wherein a possible fault is inferred if the value of the operating parameter lies outside the admissible range at two directly successive checking times, an additional check is performed to determine whether the value of the operating parameter is approaching the admissible range in a prescribed checking interval that lies between two directly successive checking times and particularly extends as far as the later of the two checking times, and it is inferred that there is a fault if the value of the operating parameter is not approaching the admissible range. 1. A method for monitoring the operation of an electricity generating installation , which comprises at least one generator that is driven by a rotating machine in order to supply electricity to an electric grid , the method comprising:acquiring and storing values of an operating parameter of the generator and/or of the rotating machine,ascertaining whether the value of the operating parameter at prescribed checking instants lies outside an admissible rangeinferring a possible fault if the value of the operating parameter lies outside the admissible range at two directly successive checking instants, and additionally checking whether the value of the operating parameter is approaching the admissible range in a prescribed checking interval that lies between the two directly successive checking instants and, in particular, extends up to the later of the two checking instants, andinferring that there is a fault if the value of the operating parameter is not approaching the admissible range.2. The method as claimed in claim 1 ,wherein checking ...

TURBINE CONTROL SYSTEM

A turbine control system is provided for decreasing the response time between readings of the speed of the turbine and changing a valve position in response thereto. The speed control system includes a speed probe that detects the speed of the turbine and a turbine valve that controls the flow of fluid or gas from or to the turbine. A controller receives a speed signal from the speed probe and sends valve position commands to the turbine valve. The controller also sends support functions to the turbine valve. The controller sends the valve position commands at a faster rate than the support functions. 1. A turbine control system , comprising:a speed probe detecting a speed of a turbine;a turbine valve controlling a flow of a fluid or a gas to or from the turbine;a controller in communication with the speed probe and the turbine valve, the controller receiving a speed signal from the speed probe, and the controller sending a first signal and a second signal to the turbine valve, the first signal comprising a valve position command to change a position of the turbine valve in response to the speed signal and the second signal comprising a support function that does not command a change in position of the turbine valve in response to the speed signal,wherein the controller outputs the first signal at a faster rate than the second signal.2. The turbine control system according to claim 1 , further comprising a speed wheel attached to and rotatable with the turbine claim 1 , the speed probe identifying teeth of the speed wheel as the teeth pass by the speed probe.3. The turbine control system according to claim 1 , further comprising a speed monitoring module claim 1 , the speed monitoring module being in communication with the speed probe claim 1 , and the speed monitoring module being in communication with the controller through an I/O bus.4. The turbine control system according to claim 1 , wherein the support function comprises a diagnostic function claim 1 , a ...

Breaker auto-synchronizer

A breaker between two electrical circuits is provided that is closed when electrical properties in both of the electrical circuits are matching. Two check circuits are provided for comparing electrical properties of the two electrical circuits. Each of the check circuits sets a corresponding authorization to close the breaker. The breaker is only closed if both check circuits set an authorization to close the circuit.

OPERATION OF AIRCRAFT ENGINES DURING TRANSIENT CONDITIONS

Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system. 1. A method for operating an aircraft engine during a transient condition of the aircraft engine , the aircraft engine including a turbine having at least a high-pressure turbine spool and a low-pressure turbine spool , the method comprising:identifying a transient condition of the aircraft engine during operation of the aircraft engine requiring one of an increase or decrease in rotational speed of the high-pressure spool;conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, providing power from a source of power separate from the aircraft engine to the high-pressure spool to at least partially accelerate the high-pressure spool during the transient condition, the source of power comprising an electrical system of an aircraft; andconditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing power from the high-pressure spool to the electrical system to at least partially decelerate the high-pressure spool during the transient condition.2. The method as defined in claim 1 , wherein the step of providing power comprises transferring power from an auxiliary power unit to the high-pressure spool.3. The method as defined in claim 1 , wherein the step of providing power comprises: ...

Tightness Test Evaluation Module For A Valve And Actuator Monitoring System

The present application provides a method of evaluating valve tightness in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include rotor acceleration and rotor speed, comparing the rotor acceleration and the rotor speed to predetermined values, and altering one or more of the operating parameters and/or initiating repair procedures if the rotor acceleration and/or the rotor speed is increasing and/or exceeds predetermined values. 1. A method of evaluating valve tightness in a turbine by a data acquisition system , comprising:receiving a plurality of operating parameters from a plurality of sensors;wherein the plurality of operating parameters comprises rotor acceleration and rotor speed;comparing the rotor acceleration and the rotor speed to predetermined values; andaltering one or more of the plurality of operating parameters and/or initiating repair procedures if the rotor acceleration and/or the rotor speed is increasing and/or exceeds predetermined values.2. The method of claim 1 , wherein the step of receiving a plurality of operating parameters comprises determining pressure claim 1 , temperature claim 1 , and/or spindle position.3. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises altering pressure claim 1 , temperature claim 1 , and/or speed.4. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises taking a valve out of service.5. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises ordering parts.6. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair ...

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 ...

A METHOD FOR MODELING A COMPRESSOR SPEED

A method is provided for modeling the compressor speed of a turbocharger, and includes determining the temperature difference across the compressor, determining the mass flow through the compressor, and calculating a compressor speed value as a function of the temperature difference across the compressor and the mass flow. 128-. (canceled)32. The method according to claim 29 , comprising:determining if a recovered exhaust gas flow is introduced downstream the compressor, and wherein the step of determining the mass flow is performed by determining the mass flow of the gas exiting the compressor and correcting the determined mass flow by a factor corresponding to recovered exhaust gas flow.33. The method according to claim 29 , wherein the step of determining the temperature difference across the compressor is performed by estimating the temperature downstream the compressor claim 29 , and by subtracting the estimated temperature from a measured ambient temperature.34. The method according to claim 33 , wherein the step of estimating the temperature downstream the compressor is performed by measuring the temperature in an air inlet manifold claim 33 , and correcting this temperature by a factor corresponding to the temperature loss across an associated cooler.35. The method according to claim 29 , comprising:determining the pressure ratio across the compressor, and wherein the step of calculating the compressor speed value is performed by calculating the compressor speed value as a function of the pressure ratio.36. The method according to claim 35 , wherein the step of determining the pressure ratio across the compressor is performed by:determining if the ambient pressure is below a preset ambient pressure corresponding to high altitude conditions, and if so, setting the ambient pressure as the preset ambient pressure, anddividing the boost pressure with the ambient pressure.37. The method according to claim 36 , wherein the step of calculating the compressor speed ...

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 ...

GAS TURBINE ENGINE UNCONTROLLED HIGH THRUST DETECTION SYSTEM AND METHOD

A system and method of detecting an uncontrolled high thrust (UHT) condition in a turbofan gas turbine engine includes processing data to determine when a current commanded fan speed value is greater than a predetermined speed value. A current UHT commanded fan speed value is processed to determine if it will cause a target fan speed value to increase, remain steady, or decrease. The target fan speed value is set equal to the current UHT commanded fan speed value when the current UHT commanded fan speed value will cause the target fan speed value to increase or remain steady, and to a deceleration threshold value when the current UHT commanded fan speed value will cause the target fan speed value to decrease. An uncontrolled high thrust alert signal is generated when actual engine fan speed exceeds the target fan speed value by a predetermined amount for a preset time period. 1. A method of detecting an uncontrolled high thrust (UHT) condition in a turbofan gas turbine engine , the method comprising the steps of:processing data to determine when a current commanded fan speed value is greater than a predetermined speed value;setting a current UHT commanded fan speed value to the greater of the current commanded fan speed value and the predetermined speed value,processing the current UHT commanded fan speed value, to determine if the current UHT commanded fan speed value will cause a target fan speed value to increase, remain steady, or decrease;setting the target fan speed value equal to (i) the current UHT commanded fan speed value when the current UHT commanded fan speed value will cause the target fan speed value to increase or remain steady, or (ii) a deceleration threshold value when the current UHT commanded fan speed value will cause the target fan speed value to decrease; andgenerating an uncontrolled high thrust alert signal when actual engine fan speed exceeds the target fan speed value by a predetermined amount for a preset time period.2. The method of ...

CONTROL LOGIC FOR GAS TURBINE ENGINE FUEL ECONOMY

A method of operating an engine of a multi-engine aircraft includes sequentially operating the engine through a plurality of cycles, each cycle including a breathing-in phase followed by a breathing-out phase. The breathing-in phase includes: i) in response to a speed of a rotor of the engine being at a sub-idle threshold, opening variable guide vanes upstream a compressor and injecting fuel into the combustor to increase rotor speed to a pre-determined upper threshold, and then ii) in response to the rotor speed reaching the pre-determined upper threshold, reducing a supply rate of fuel into the combustor and substantially closing the variable guide vanes. The breathing-out phase includes maintaining the variable guide vanes closed at least until the speed drops from the pre-determined upper threshold to the pre-determined sub-idle threshold. 1. A method of operating an engine of a multi-engine aircraft , comprising:sequentially operating the engine through a plurality of cycles, a given cycle of the plurality of cycles including a breathing-in phase followed by a breathing-out phase, i) in response to a speed of a rotor of the engine being at a sub-idle threshold, opening a set of variable guide vanes upstream an air compressor section of the engine and injecting a fuel into a combustor of the engine to increase the speed to at least approximately a pre-determined upper threshold, and then', 'ii) in response to the speed reaching the pre-determined upper threshold, at least reducing a supply rate of the fuel into the combustor and at least substantially closing the set of variable guide vanes,', 'the breathing-out phase including maintaining the set of variable guide vanes closed at least until the speed drops from the pre-determined upper threshold to at least approximately the pre-determined sub-idle threshold., 'the breathing-in phase including2. The method of claim 1 , wherein in the breathing-in phase of at least one repeating cycle of the plurality of cycles ...

METHOD AND SYSTEM FOR ADJUSTING ENGINE CYLINDER OPERATION

Various methods and systems are provided for diagnosing individual engine cylinders based on a turbocharger speed fluctuation of a turbocharger. In one embodiment, a method for an engine includes adjusting engine operation based on an indicated operating parameter of an individual engine cylinder, where the indicated operating parameter is based on at least one turbocharger speed fluctuation of a turbocharger correlated with crankshaft position. 1. A method for an engine , comprising:adjusting engine operation based on an indicated operating parameter of an individual engine cylinder, where the indicated operating parameter is based on at least one turbocharger speed fluctuation of a turbocharger correlated with crankshaft position of a crankshaft.2. The method of claim 1 , wherein the indicated operating parameter includes one or more of engine misfire claim 1 , engine knock claim 1 , total fueling amount that is above or below a threshold value range claim 1 , fueling ratio between a first and second fuel in a multi-fuel system claim 1 , degradation of the individual engine cylinder claim 1 , degradation of a fuel injector that is configured to supply fuel to the individual engine cylinder claim 1 , or degradation of an exhaust valve of the individual engine cylinder.3. The method of claim 1 , wherein the turbocharger speed fluctuation of the turbocharger is an instantaneous turbocharger speed fluctuation of the turbocharger; and claim 1 , further comprising determining a magnitude and timing of the instantaneous turbocharger speed fluctuation for the individual engine cylinder and determining the indicated operating parameter of the individual engine cylinder based on one or more of the determined magnitude or the timing being outside of a corresponding one or more determined threshold ranges.4. The method of claim 3 , wherein the threshold ranges are based at least in part on an average magnitude of the instantaneous turbocharger speed fluctuation for each and ...

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.

MAGNETIC SENSING SYSTEM AND METHOD FOR DETECTING SHAFT SPEED

A sensing system for sensing rotational speed of a shaft in a gas turbine engine, comprising: a target, the target fixed to the shaft in use, the target comprising at least one ferrous target element radially spaced from the shaft, and a first magnetic probe assembly comprising a first pole piece element and a second pole piece element, wherein the first pole piece element and the second pole piece element are radially spaced from one another so that the at least one ferrous target element passes proximate to and between the first and second pole piece elements as the target rotates, so that radial movement of the at least one ferrous target element away from one of the first and second pole piece elements results in simultaneous and corresponding radial movement of the at least one ferrous target element towards the other of the first and second pole piece elements. By providing pole piece elements that are radially spaced from each other, radial movement of the target away from one pole piece element as a result of eccentric rotation of the shaft is compensated for by corresponding movement of the target towards the other pole piece element. 1. A sensing system for sensing rotational speed of a shaft in a gas turbine engine , comprising:a target, the target fixed to the shaft in use, the target comprising at least one ferrous target element radially spaced from the shaft;a first magnetic probe assembly comprising a first pole piece element and a second pole piece element, wherein the first pole piece element and the second pole piece element are radially spaced from one another so that the at least one ferrous target element passes proximate to and between the first and second pole piece elements as the target rotates, so that radial movement of the at least one ferrous target element away from one of the first and second pole piece elements results in simultaneous and corresponding radial movement of the at least one ferrous target element towards the other of ...

Systems and Methods for Boundary Control During Steam Turbine Acceleration

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

Blade angle position feedback system with embedded markers

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

ROTARY MACHINE

Provided is a rotary machine in which the output of a magnetic sensor is hardly lowered even if the rotation speed of a rotor becomes high. The rotary machine includes a rotor, a housing, a magnet, and a magnetic sensor. The rotor axially rotates around a rotation axis. The housing is formed of a conductive material and contains the rotor. The magnet is attached to the rotor such that an arrangement direction of a pair of magnetic poles is in a radial direction of the rotor. The magnetic sensor is attached to the housing. The magnetic sensor detects a time variation of a magnetic field generated from the magnet to detect the rotation speed of the rotor. The magnetic sensor is located on the outside than the magnet in the radial direction. The magnetism sensing direction of the magnetic sensor is orthogonal to the radial direction. 1. A rotary machine comprising:a rotor configured to axially rotate around a rotation axis;a housing formed of a conductive material and containing the rotor;a magnet attached to the rotor such that an arrangement direction of at least a pair of magnetic poles is in a radial direction of the rotor; anda magnetic sensor attached to the housing and configured to detect a time variation of a magnetic field generated from the magnet to thereby detect a rotation speed of the rotor,wherein the magnetic sensor is arranged on the outside than the magnet in the radial direction, andwherein a magnetism sensing direction of the magnetic sensor is orthogonal to the radial direction.2. The rotary machine according to claim 1 , wherein the magnetic sensor is arranged at a position apart from the magnet by a prescribed distance in an axial direction of the rotor.3. The rotary machine according to claim 1 , wherein the magnetic sensor is located on the inside than an intermediate position between an exterior surface and an interior surface of the housing in the radial direction.4. The rotary machine according to claim 2 , wherein the magnetic sensor is ...

SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE

A method for a gas turbine engine includes affixing a speed sensor probe in the gas turbine engine. The sensor probe is operable to determine a rotational speed in the gas turbine engine. The gas turbine engine includes a first spool that is coupled at a first axial position to a compressor hub that is coupled to drive a first compressor. The first spool is coupled at a second, different axial position to a fan drive input shaft that is coupled to drive a fan drive gear system. The second turbine is coupled through a second spool to drive a second compressor. The speed sensor probe is affixed at a third axial position that is axially forward of the first axial position and axially aft of the second axial position. 1. A method for a gas turbine engine , the method comprising:affixing a speed sensor probe in a gas turbine engine, the sensor probe operable to determine a rotational speed in the gas turbine engine, the gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan about an engine central axis, a compressor section including a first compressor and a second compressor, and a turbine section that includes a first turbine and a second turbine, the first turbine coupled to drive a first spool, the first spool being coupled at a first axial position to a compressor hub that is coupled to drive the first compressor and the first spool being coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system, and the second turbine coupled through a second spool to drive the second compressor, andthe speed sensor probe being affixed at a third axial position that is axially forward of the first axial position and axially aft of the second axial position.2. The method as recited in claim 1 , including claim 1 , prior to affixing the speed sensor probe claim 1 , removing a used speed sensor probe from the gas turbine engine such that the affixed speed sensor probe replaces the used speed ...

LASER MEASUREMENT SYSTEM FOR DETECTING TURBINE BLADE LOCKUP

A laser measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one laser device for emitting a laser beam that impinges on a blade surface of each blade in a row of blade assemblies. The laser beam is also transmitted through a space between adjacent blades to impinge on corresponding internal surfaces of the gas turbine. Further, the system includes a photon detector for detecting a first time period in which first laser energy is reflected from each blade surface and a second time period in which second laser energy is reflected from each internal surface and transmitted through each space. The system also includes a controller for detecting a change in at least one second time period to indicate that a distance between consecutive blades has changed and that at least one locked blade assembly is locked. 1. A laser measurement system for detecting at least one locked blade assembly in a gas turbine having a plurality of blade assemblies arranged in rows wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades , comprising:at least one laser device for emitting a laser beam that impinges on a blade surface of each blade in a row of blades and wherein the laser beam is also transmitted through each space between adjacent blades to impinge on corresponding internal surfaces of the gas turbine;a photon detector for detecting a first time period in which first laser energy is reflected from each blade surface and a second time period in which second laser energy is reflected from each internal surface and transmitted through each space to provide a plurality of first and second time periods; anda controller for controlling operation of the laser device and photon detector wherein detection of a change in at least one second time period relative to remaining second time periods indicates that a distance between ...

Methods and systems to monitor health of rotor blades

A system for monitoring health of a rotor is presented. The system includes a processing subsystem that generates a plurality of frequency peak values corresponding to two or more respective windows of signals by iteratively shifting the two or more respective windows of signals along delta times of arrival signals corresponding to a blade in the rotor, determines one or more resonant-frequency rotor speeds ranges of the blade by identifying rotor speeds corresponding to a subset of the plurality of frequency peak values, and monitors the blade to determine a presence of one or more defects in the blade during the resonant-frequency rotor speeds regions.

Methods and systems for monitoring rotor blades in turbine engines

A method for determining an arrival-time of a rotor blade that includes attaching an RF reader to a stationary surface and an RF tag to the rotor blade. Strength-of-signal data points are collected via an RF monitoring process that includes: emitting an RF signal from the RF reader; receiving the RF signal at the RF tag and emitting a return RF signal by the RF tag in response thereto; receiving the return RF signal at the RF reader; measuring a signal strength of the return RF signal as received by the RF reader; and determining the strength-of-signal data point as being equal to the measured signal strength. The RF monitoring process is repeated until multiple strength-of-signal data points are collected. A maximum strength-of-signal is determined from the multiple strength-of-signal data points, and the arrival-time for the rotor blade is determined as being a time that corresponds to the maximum strength-of-signal.

Methods and systems for monitoring rotor blades in turbine engines

A method for determining an arrival-time of a rotor blade in a turbine engine that includes the steps of: having an RF reader attached to a stationary surface in the turbine engine; having an RF tag attached to a first region of the rotor blade; having a reference RF tag attached to a rotating structure near the RF tag; in relation to a first revolution of the rotor blade occurring during the operation of the turbine engine, collecting an arrival-time for each of the RF tag and the reference RF tag with the RF reader via an RF monitoring process; comparing the arrival-time of the RF tag to the arrival-time of the reference RF tag to determine an arrival-time test result for the first region of the rotor blade for the first revolution.

Adaptive Voltage Threshold for Turbine Engine

The subject matter of this specification can be embodied in, among other things, a method for controlling a turbine engine that includes receiving a predetermined arming threshold signal, receiving a predetermined triggering threshold signal, receiving a periodic signal from a speed sensor, determining a frequency signal based on the periodic signal, the predetermined arming threshold signal, and the predetermined triggering threshold signal, determining a speed value based on the determined frequency signal, and controlling a speed of a turbine based on the determined speed value. 1. A method for controlling a turbine engine , the method comprising:receiving a predetermined arming threshold signal;receiving a predetermined triggering threshold signal;receiving a periodic signal from a speed sensor;determining a frequency signal based on the periodic signal, the predetermined arming threshold signal, and the predetermined triggering threshold signal;determining a speed value based on the determined frequency signal; andcontrolling a speed of a turbine based on the determined speed value.2. The method of claim 1 , wherein determining the frequency signal comprises:monitoring the periodic signal;determining that the periodic signal has satisfied an arming threshold based on the predetermined arming threshold signal;arming a trigger based on the determined satisfaction of the predetermined arming threshold;triggering an output signal based on determining that the trigger is armed and that the periodic signal has satisfied a triggering threshold based on the predetermined triggering threshold signal; andproviding the frequency signal based on the output signal.3. The method of claim 1 , wherein determining the speed value based on the determined frequency signal comprises:determining a periodicity of the determined frequency signal; anddetermining the speed value based on the determined periodicity.4. The method of claim 1 , further comprising determining 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 ...

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.

SYSTEM AND METHOD FOR CONTROLLING A GAS TURBINE ENGINE

A control system for a gas turbine engine including a power turbine is disclosed. The control system may include a control module to receive engine operating goals and an estimated current engine state, wherein the estimated current engine state is produced by a model-based estimation module using a bandwidth signal produced by an adaptation logic module. The control module is operative to determine fuel flow, inlet guide vane schedules and stability bleed schedules based at least in part on the received engine operating goals and the estimated current engine state, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow, inlet guide vane schedules and stability bleed schedules. 1. A control system for a gas turbine engine , the control system comprising:a first sensor configured to generate a thrust lever angle signal indicative of a thrust lever angle commanded of the gas turbine engine;a second sensor in communication with the gas turbine engine and configured to generate at least one operating parameter signal indicative of at least one operating parameter of the gas turbine engine;a power rating module configured to receive the thrust lever angle signal and generate at least one goal signal indicative of an operating point goal for the gas turbine engine;an adaptation logic module configured to receive the at least one goal signal and the at least one operating parameter signal and generate a bandwidth signal indicative of an error between the at least one goal signal and the at least one operating parameter signal;a model-based estimation module configured to receive the bandwidth signal and generate an engine estimate signal indicative of estimated current engine parameters of the gas turbine engine based at least in part on the bandwidth signal; anda model-based control module configured to receive the at least one operating parameter signal, the at least one goal signal, ...

Shaft monitoring system

A system for monitoring the axial position of a rotating shaft includes a phonic wheel mounted coaxially to the shaft for rotation with a circumferential row of teeth. The system includes a sensor configured to detect the passage of the teeth by generating an alternating measurement signal. First and second portions of the teeth alternate around the row and contribute respective first and second components to the alternating measurement signal. The first portion of teeth vary in height in an axial direction of the wheel such that the relative height of the first and second portions varies with axial distance across the phonic wheel, and the sensor is positioned relative to the phonic wheel such that axial displacement of the shaft causes the signal to vary the first component's amplitude relative to the second component's amplitude due to the height variation, to monitor the axial position of the shaft.

CONTROL OF COMBUSTION ENGINE SHUT DOWN

The abrupt cessation or run-away of a combustion engine may damage the combustion engine and pose a safety hazard to the surrounding environment. The combustion engine operational mode may be controlled, regulated or maintained by regulating the combustion mixture of the combustion engine. The oxidizer flow, a material or both of the combustion mixture may be regulate to create or form a combustion material that is outside a combustible range such that the combustion engine is placed or maintained in a spin-down operational mode. The material added to the combustion mixture may include a combustible, non-combustible, oxidizer, or exhaust material. A brake may also provide a secondary mechanism to maintain or place the combustion engine in a spin-down mode. 1. A combustion engine system , comprising:a combustion engine;an intake vent disposed about the combustion engine;a control damper disposed about the intake vent, wherein the control damper controls oxidizer flow to the intake vent; anda combustion mixture, wherein the combustion mixture comprises a portion of oxidizer and a portion of fuel, wherein the portion of oxidizer is restricted by the control damper such that the combustion mixture is within a non-combustible range to maintain the combustion engine in a spin-down operational mode.2. The combustion engine system of claim 1 , further comprising a sensor disposed about the control damper claim 1 , wherein the sensor transmits one or more measurements associated with oxidizer flow to the intake vent to a control panel.3. The combustion engine system of claim 2 , wherein the control panel is communicatively coupled to the control damper claim 2 , and wherein the control panel adjusts a position of control damper based claim 2 , at least in part claim 2 , on the one or more measures associated with the oxidizer flow.4. The combustion engine system of claim 1 , further comprising a brake disposed about the combustion engine claim 1 , wherein the brake prevents ...

AIRFLOW CONTROL FOR AIR TURBINE STARTER

An example arrangement for cooling a gas turbine engine includes an air turbine starter having a turbine section for rotationally driving a compressor through rotation of a shaft. An starter air valve is configured to control a flow of pressurized air that flows downstream towards turbine blades of the air turbine starter. An airflow adjustment device (AAD) is configured to adjust the flow when a manual override feature of the starter air valve is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor. A governor is configured to control a degree to which the AAD adjusts the flow. The governor is mechanically linked to the shaft through one or more gears and configured to adjust the AAD such that a rotational speed of said one the shafts does not exceed a predefined threshold during a particular operating mode. 1. An arrangement for cooling a gas turbine engine comprising:an air turbine starter comprising a turbine section for rotationally driving a compressor of a gas turbine engine through rotation of a shaft that connects the turbine section to the compressor;a starter air valve configured to control a flow of pressurized air along a flow path that flows downstream towards turbine blades of the turbine section, the starter air valve having a manual override feature that allows manual opening of the starter air valve;an airflow adjustment device configured to adjust the flow of pressurized air along the flow path when the manual override feature is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor; anda governor configured to control a degree to which the airflow adjustment device adjusts the flow, the governor mechanically linked to the shaft through one or more gears and configured to adjust the airflow adjustment device such that a rotational speed of said one of the shafts does not exceed a predefined threshold during a particular operating ...

TURBO ROTATION SENSOR AND TURBOCHARGER

A turbo rotation sensor includes a magnet magnetized with two different magnetic poles along a circumferential direction about a rotating shaft of a compressor wheel and provided at an end portion of the compressor wheel on the air intake side, and a sensor portion that is housed in a sensor hole formed on the housing, is arranged to face the magnet in a radial direction of the rotating shaft, and includes two magnetic field detecting elements capable of measuring variation in magnetic flux density caused by the magnet. The two magnetic field detecting elements are aligned in a direction parallel to the rotating shaft so that the respective detection axes are parallel to an axial direction of the rotating shaft. The rotational speed of the compressor wheel is detected based on a difference between the magnetic field strengths detected by the two magnetic field detecting elements. 1. A turbo rotation sensor for being mounted on a turbocharger to detect a rotational speed of a compressor wheel , the turbocharger comprising a turbine provided on an exhaust gas path of a vehicle internal combustion engine and comprising a turbine wheel rotationally driven by exhaust gas from the internal combustion engine and a compressor provided on an air intake path of the internal combustion engine and comprising the compressor wheel rotationally driven by rotation of the turbine wheel and a housing for housing the compressor wheel , the turbo rotation sensor comprising:a magnet magnetized with two different magnetic poles along a circumferential direction about a rotating shaft of the compressor wheel and provided at an end portion of the compressor wheel on the air intake side so as to rotate together with the compressor wheel; anda sensor portion that is housed in a sensor hole formed on the housing, is arranged to face the magnet in a radial direction of the rotating shaft, and comprises two magnetic field detecting elements capable of measuring variation in magnetic flux ...

SYSTEM AND METHOD FOR CONTROLLING DUAL STARTER AIR VALVE

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor. 1. A system , comprising:a sensor configured to measure a characteristic of an engine component; and a first valve,', 'a first valve control device coupled to the first valve and configured to control the first valve based on a measurement by the sensor,', 'a second valve in fluidic series with the first valve, and', 'a second valve control device coupled to the second valve and configured to control the second valve based on the measurement by the sensor., 'a valve assembly having an airflow outlet in fluid communication with the engine component, the valve assembly including2. The valve assembly of claim 1 , wherein the first valve control device comprises a torque motor servovalve and wherein the torque motor servovalve is configured to adjust a position of the first valve in response to an input of a current.3. The valve assembly of claim 2 , wherein the first valve comprises a first piston claim 2 , and wherein a position of the first piston is configured to control an output pressure of air at the airflow outlet.4. The valve assembly of claim 1 , wherein the second valve control device comprises a solenoid and wherein the solenoid is configured to open or close the second valve.5. The valve assembly of claim 4 , wherein the second valve comprises a second piston claim 4 , and wherein a position of the second piston is configured to control an output pressure of air at the airflow ...

Speed Sensor Insert With Bearing Spacer Indexing For A Turbocharger

Modern turbochargers use speed sensors to determine the shaft speed during operation. In order to replace a speed sensor in a turbocharger with journal bearings separated by a spacer, the tip of the speed sensor must be withdrawn from a window in the spacer and replaced through the same window. If the spacer turns while the sensor is removed, then the window will be out of alignment with the axis of the sensor and the sensor cannot be re-inserted through the window. An insert is provided for preventing rotation of the window in the spacer while the sensor is withdrawn. The insert also prevents wear to the speed sensor from the fluctuating contact forces transmitted from the shaft to the bearing spacer and subsequently to the speed sensor. Accordingly, the durability of the speed sensor is improved, the rate of failure and need for sensor replacement, is reduced. 1. A turbocharger bearing housing , includinga bearing bore,a rolling element bearing assembly including an inner race and an outer race having a plurality of ball bearing disposed therebetween, wherein the rolling element bearing assembly is disposed within the bearing bore,a shaft for rotating the rolling element bearing assembly, located and supported within the inner race,a tubular bearing spacer having first and second axial ends, and at least one radial opening,a mounting bore,a generally tubular insert mounted in the mounting bore and extending into the opening in the opening of the bearing spacer, anda rotational speed sensor mounted to the tubular insert via threaded fitting or friction fit.2. The turbocharger as in claim 1 , wherein the generally tubular insert is mounted in the mounting bore by a screw fit claim 1 , a friction fit claim 1 , a pressed fit or by bonding claim 1 , staking claim 1 , or welding.3. The turbocharger as in claim 1 , wherein the tubular insert and speed sensor are provided with indexing features for setting the depth of penetration of the speed sensor.4. The turbocharger ...

METHOD FOR MANAGING A BREAKDOWN OF A TURBINE ENGINE STARTER VALVE

The present invention concerns a method () for managing a breakdown of a starter valve of a starting circuit of an aircraft turbine engine, comprising the following steps: —starting () the turbine engine, a state-change command being sent to the starter valve in order for it to open;—increasing () the engine speed of the turbine engine to a predefined first threshold,—during said increase () in engine speed,—if a difference in position has been detected () between the position sensors before the step of starting the turbine engine or if a difference in position is detected () between said position sensors, determining () the position sensor that has switched between the closed position and the open position, the other position sensor having remained in the open or closed position;—when the first threshold is reached, storing () the position sensor that has switched between the closed position and the open position as healthy and the position sensor that has remained in the open or closed position as faulty, so as to measure the state of the starter valve only on the basis of the position of the healthy position sensor. 2. The method according to claim 1 , wherein it is verified claim 1 , during the initiation of the starting of the turbine engine or when the turbine engine has reached the first threshold claim 1 , that a difference is still detected between the positions of the position sensors.3. The method according to claim 1 , wherein the engine speed corresponds to the speed of rotation of a high-pressure shaft of the turbine engine.4. The method according claim 1 , wherein when the turbine engine reaches the first threshold claim 1 , a combustion chamber of the turbine engine is not yet lit.5. The method according to claim 1 , further comprising the steps of:lighting a combustion chamber of the turbine engine;increasing the engine speed of the turbine engine until a second predetermined threshold; sending a state change command to the starter air valve so that ...

STARTER AIR VALVE SYSTEMS CONFIGURED FOR LOW SPEED MOTORING

A starter air valve (SAV) system can include a pressure actuated SAV actuator configured to be operatively connected to a SAV and a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator. The first pressure valve can be a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator. 1. A starter air valve (SAV) system comprising:a pressure actuated SAV actuator configured to be operatively connected to a SAV; anda first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator;wherein the first pressure valve is a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator.2. The system of claim 1 , wherein the SAV includes at least one of a butterfly valve or an inline valve.3. The system of claim 1 , further comprising a first controller in operable communication with at least the first pressure valve and configured to control the first pressure valve.4. The system of claim 3 , wherein the first controller is an engine computer.5. The system of claim 3 , further comprising a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator.6. The system of claim 5 , further comprising a second controller in operable communication with at least the second pressure valve and configured to control the second pressure valve.7. The system of claim 6 , a manual override (MOR) valve selector disposed between the first pressure valve claim 6 , the second pressure valve claim 6 , and the SAV actuator claim 6 , the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly ...

AIR TURBINE STARTER WITH AUTOMATED VARIABLE INLET VANES

According to one embodiment, an air turbine starter is provided. The air turbine starter comprising: a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub; an inlet housing at least partially surrounding the turbine wheel; a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades; and a plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing; wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane. 1. An air turbine starter comprising:a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub;an inlet housing at least partially surrounding the turbine wheel;a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades; anda plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing;wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane.2. The air turbine starter of claim 1 , further comprising:at least one actuator operably connected to at least one turbine vane, the at least one actuator in operation rotates at least one turbine vane.3. The air turbine starter of claim 2 , wherein:the at least one actuator is at least one of a pneumatic actuator, an electric actuator, and a hydraulic actuator.4. The air turbine starter ...

Device and method for protecting an aircraft turbomachine computer against speed measurement errors

A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor. Analyzing the error signals, exceeding the determined deviation can control stopping the turbomachine.

Rotary actuator and application thereof

A specially designed rotary actuator comprising a sealed container and a piston rotor located in the sealed container. The piston rotor divides the sealed container into a first space and a second space having different pressures. The first end of the piston rotor faces the first space and includes a plurality of first bores, and the second end of the piston rotor faces the second space and includes a plurality of second bores. The depth of the first and second bores is less than the thickness of the piston rotor. Each of the first and second bores comprises a first portion and a second portion, wherein the surface area of the first portion is greater than the surface area of the second portion.

Speed sensor for a gas turbine engine

A gas turbine engine includes a speed change mechanism. A fan drive shaft has a radially extending surface that is attached to the speed change mechanism. A speed sensor is located adjacent the radially extending surface.

POWER SOURCE, ADJUSTING POWER INSTRUCTING APPARATUS, METHOD, AND RECORDING MEDIUM FOR CHANGING ADJUSTING POWER

A power source includes: a generator; a turbine device that drives and rotates the generator; and a control device that: monitors a rotation speed of the generator; calculates a first adjusting power instruction value corresponding to a deviation between a reference value and an observed value of the rotation speed of the generator; acquires an adjusting power amplification coefficient from an external device; calculates a second adjusting power instruction value indicating a degree of increase of the adjusting power, based on the first adjusting power instruction value and the adjusting power amplification coefficient; amplifies the adjusting power based on the second adjusting power instruction value; and outputs the amplified adjusting power to the turbine device to adjust power supply from the generator and reduces fluctuation of frequency in a power transmission and distribution system. 1. A power source comprising:a generator;a turbine device that drives and rotates the generator; and monitors a rotation speed of the generator;', 'calculates a first adjusting power instruction value corresponding to a deviation between a reference value and an observed value of the rotation speed of the generator;', 'acquires an adjusting power amplification coefficient from an external device;', 'calculates a second adjusting power instruction value indicating a degree of increase of the adjusting power, based on the first adjusting power instruction value and the adjusting power amplification coefficient;', 'amplifies the adjusting power based on the second adjusting power instruction value; and', 'outputs the amplified adjusting power to the turbine device to adjust power supply from the generator and reduces fluctuation of frequency in a power transmission and distribution system., 'a control device that2. The power source according to claim 1 , wherein calculates an amplified adjusting power instruction value by adding the first adjusting power instruction value and the ...

RECOVERING SPEED IN DRIVELINE ASSEMBLY

Aspects of the disclosure include apparatuses and program products for recovering speed in a driveline assembly. An apparatus in one embodiment may include: a sensor measuring a shaft speed of a rotatable shaft within a driveline assembly, wherein the driveline assembly includes: a load coupled to the rotatable shaft, a primary power source coupled to the load through the rotatable shaft to deliver a first power output to the load, and a secondary power source coupled to the load through the rotatable shaft to deliver a second power output to the load, wherein the second power output is less than the first power output; and a controller in communication with the secondary power source and the sensor, wherein the controller increases the second power output in response to the shaft speed being less than a minimum speed threshold. 1. An apparatus comprising: a load coupled to the rotatable shaft,', 'a primary power source coupled to the load through the rotatable shaft to deliver a first power output to the load, and', 'a secondary power source coupled to the load through the rotatable shaft to deliver a second power output to the load, wherein the second power output is less than the first power output; and, 'a sensor measuring a shaft speed of a rotatable shaft within a driveline assembly, wherein the driveline assembly includesa controller in communication with the secondary power source and the sensor, wherein the controller increases the second power output in response to the shaft speed being less than a minimum speed threshold.2. The apparatus of claim 1 , wherein the secondary power source comprises a motor claim 1 , and the controller is further configured to modify a power set point of the motor.3. The apparatus of claim 1 , wherein the driveline assembly further includes a torque converter coupled to the secondary power source and the rotatable shaft claim 1 , and the controller further modifies a conversion factor of the torque converter to increase or ...

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 ...

Anti-Windmilling Starter Generator

An APU has a gas turbine engine and a starter generator to be selectively driven by the gas turbine engine. A sensor senses windmilling of components associated with the starter generator. A lock feature limits rotation within the starter generator when windmilling is sensed. A method of operation is also disclosed. 1. An auxiliary power unit (APU) comprising:a gas turbine engine, and a starter generator to be selectively driven by said gas turbine engine; anda sensor for sensing windmilling associated with said starter generator, and a lock feature for limiting rotation within said starter generator when windmilling is sensed.2. The APU as set forth in claim 1 , wherein said starter generator is connected into a gearbox claim 1 , and said sensor sensing rotation of a gear within said gearbox.3. The APU as set forth in claim 1 , wherein said starter generator includes a DC powered stator and rotor claim 1 , and said lock feature includes a selective supply of AC power to said stator to limit said rotor from rotation relative to said stator.4. The APU as set forth in claim 3 , wherein a control selectively communicates AC power to said stator only when windmilling is sensed.5. An auxiliary power unit (APU) and air supply system comprising:a gas turbine engine, and a starter generator to be selectively driven by said gas turbine engine;a sensor for sensing undesired rotation of components associated with said starter generator, and a lock feature for limiting rotation of said components within said starter generator when undesired rotation is sensed; andthe lock feature including a supply of AC power into a DC powered stator associated with a DC powered rotor, and a control communicating with said sensor, and receiving a signal when undesired rotation is sensed to supply AC power to said stator.6. The APU and air supply system as set forth in claim 5 , wherein said starter generator is connected into a gearbox claim 5 , and said sensor sensing undesired rotation of a ...

TURBINE ASSEMBLY WITH AUXILIARY WHEEL

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc. 1. A turbine assembly comprising:a turbine disc connected to a coaxial central shaft;an auxiliary wheel secured to the turbine disc and coaxial with the central shaft, the auxiliary wheel comprising an annular target portion, the target portion comprising a plurality of first features and a plurality of different second features, the plurality of first features alternating with the plurality of second features about a circumference of the annular target portion;a speed sensing system comprising a probe and a controller, the speed sensing system being configured to estimate a rotational speed of the turbine disc based on a rate that the plurality of first features and the plurality of second features are carried past the probe.2. The turbine assembly of claim 1 , where the coaxial central shaft is a spool claim 1 , the turbine disc is non-magnetic claim 1 , the auxiliary wheel is magnetic such that both the plurality of first features and the plurality of different second features are magnetic claim 1 , and the probe comprises a magnet.3. The turbine assembly of claim 2 , further comprising a clamping disc coaxial with the spool and the turbine disc claim 2 , the clamping disc coupling the turbine disc with the central shaft.4. The turbine assembly of claim 1 , wherein the plurality of first features are teeth and the plurality of second features are channels defined between consecutive teeth.5. The turbine assembly of claim 1 , wherein the plurality of first features are magnetic and the probe comprises a magnet.6. The turbine assembly of claim 5 , wherein the probe is configured to generate a first magnetic field when the probe is proximate to the one of the ...

GAS TURBINE ENGINE UNCONTROLLED HIGH THRUST ACCOMMODATION SYSTEM AND METHOD

A system and method of accommodating an uncontrolled high thrust condition in a turbofan gas turbine engine includes processing engine data from the turbofan gas turbine engine to determine when a potential for an uncontrolled high thrust condition exists. When the potential for an uncontrolled high thrust condition exists, the engine data are processed to determine whether corrective action for the uncontrolled high thrust condition should be implemented by varying turbofan gas turbine engine effective geometry to (i) increase turbofan gas turbine engine rotational speed or (ii) decrease turbofan gas turbine engine rotational speed. The determined corrective action is automatically implemented. 1. A method of accommodating an uncontrolled high thrust condition in a turbofan gas turbine engine , the method comprising the steps of:processing engine data from the turbofan gas turbine engine to determine when a potential for an uncontrolled high thrust condition exists;when the potential for an uncontrolled high thrust condition exists, processing the engine data to determine whether corrective action for the uncontrolled high thrust condition should be implemented by varying turbofan gas turbine engine effective geometry to (i) increase turbofan gas turbine engine rotational speed or (ii) decrease turbofan gas turbine engine rotational speed; andautomatically implementing the determined corrective action.2. The method of claim 1 , further comprising:when the potential for an uncontrolled high thrust condition exists, processing the engine data to determine if the turbofan gas turbine engine rotational speed will reach an overspeed trip limit by closing inlet guide vanes in the turbofan gas turbine engine; andif so, closing the inlet guide vanes to increase the turbofan gas turbine engine rotational speed to the overspeed trip limit.3. The method of claim 2 , wherein:the engine data include high pressure turbine rotational speed; andthe overspeed trip limit is ...

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 ...

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 ...

TURBO ROTATION SENSOR

A turbo rotation sensor, which is configured to be mounted on a turbocharger provided with a compressor including a rotary driven compressor wheel housed in a compressor housing, to detect rotation speed of the compressor wheel, is composed of a magnet rotatable integrally with the compressor wheel and having a plurality of magnetic poles in a circumferential direction of the compressor wheel, and a sensor section attached to the compressor housing and including first and second magnetic detection elements capable of detecting a magnetic field in a radial direction of the compressor wheel due to the magnet. The first and second magnetic detection elements are arranged side by side in the radial direction of the compressor wheel. The rotation speed of the compressor wheel can be measured based on a difference between detection results of the first and second magnetic detection elements resulting from a difference between their respective distances from the magnet. 1. A turbo rotation sensor , which is configured to be mounted on a turbocharger provided with a compressor including a rotary driven compressor wheel housed in a compressor housing , to detect rotation speed of the compressor wheel , comprising:a magnet rotatable integrally with the compressor wheel and having a plurality of magnetic poles in a circumferential direction of the compressor wheel; anda sensor section attached to the compressor housing and including first and second magnetic detection elements capable of detecting a magnetic field in a radial direction of the compressor wheel due to the magnet,wherein the first and second magnetic detection elements are arranged side by side in the radial direction of the compressor wheel,wherein the rotation speed of the compressor wheel can be measured based on a difference between detection results of the first and second magnetic detection elements resulting from a difference between their respective distances from the magnet.2. The turbo rotation sensor ...

METHOD FOR MODELING A COMPRESSOR SPEED

A method is provided for modeling the compressor speed of a turbocharger, and includes determining the temperature difference across the compressor, determining the mass flow through the compressor, and calculating a compressor speed value as a function of the temperature difference across the compressor and the mass flow. 4. The method according to claim 1 , comprising:determining if a recovered exhaust gas flow is introduced downstream the compressor, and wherein the step of determining the mass flow is performed by determining the mass flow of the gas exiting the compressor and correcting the determined mass flow by a factor corresponding to recovered exhaust gas flow.5. The method according to claim 1 , wherein the step of determining the temperature difference across the compressor is performed by estimating the temperature downstream the compressor claim 1 , and by subtracting the estimated temperature from a measured ambient temperature.6. The method according to claim 5 , wherein the step of estimating the temperature downstream the compressor is performed by measuring the temperature in an air inlet manifold claim 5 , and correcting this temperature by a factor corresponding to the temperature loss across an associated cooler.7. The method according to claim 1 , comprising:determining the pressure ratio across the compressor, and wherein the step of calculating the compressor speed value is performed by calculating the compressor speed value as a function of the pressure ratio.8. The method according to claim 7 , wherein the step of determining the pressure ratio across the compressor is performed by:determining if the ambient pressure is below a preset ambient pressure corresponding to high altitude conditions, and if so, setting the ambient pressure as the preset ambient pressure, anddividing the boost pressure with the ambient pressure.9. The method according to claim 8 , wherein the step of calculating the compressor speed value is performed by ...

CONTROL LOGIC FOR GAS TURBINE ENGINE FUEL ECONOMY

A method of operating a multi-engine aircraft includes operating a first engine of the aircraft to provide motive power; and operating a second engine of the aircraft in a standby mode to provide substantially no motive power, a rotor of the second engine having an idle rotational speed in the standby mode, and in the standby mode, sequentially executing cycles, a given cycle of the cycles including: opening a set of variable guide vanes upstream a compressor section of the second engine, spiking a rate of a fuel flow to a combustor of the second engine, the spiking and the opening timed to increase a rotational speed of the rotor of the second engine to an upper threshold above the idle rotational speed of the rotor, and in response to the rotational speed reaching the upper threshold, at least substantially closing the set of variable guide vanes. 1. A method of operating a multi-engine aircraft having a first engine and a second engine operable to power the aircraft , the second engine having a rotor operable at a substantially constant idle rotational speed resulting from a substantially constant idle fuel supply rate to a combustor of the second engine , comprising:operating the first engine of the multi-engine aircraft to provide motive power to the aircraft; and in response to a rotational speed of the rotor of the second engine reaching a threshold below the substantially constant idle rotational speed, modulating a set of variable guide vanes upstream a compressor section of the second engine toward a fully open position,', 'at least in part concurrently with the modulating toward the open position, spiking a rate of a fuel flow to a combustor of the second engine, the spiking and the opening timed to increase a rotational speed of the rotor of the second engine to a threshold above the substantially constant idle rotational speed, and', 'in response to the rotational speed reaching the upper threshold, modulating the set of variable guide vanes toward a ...

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 ...

SYSTEM AND METHOD FOR CONTROLLING DUAL STARTER AIR VALVE

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor. 1. A method of controlling a rotational speed of a gas turbine engine during start-up , comprising:receiving, by a valve assembly, an input airflow having an input pressure, the valve assembly including a first valve and a second valve;measuring the rotational speed of the gas turbine engine;controlling, by a full authority digital engine control (FADEC), an output pressure of an output airflow by controlling a position at least one of the first valve and the second valve based on the rotational speed of the gas turbine engine; anddelivering the output airflow to an air turbine starter coupled to the gas turbine engine.2. The method of claim 1 , wherein the first valve comprises a torque motor servovalve and wherein the positioning the at least one of the first valve and the second valve further comprises delivering a current to the torque motor servovalve to adjust the position of the first valve.3. The method of claim 2 , wherein the positioning the at least one of the first valve and the second valve further comprises locking the second valve in an open position while adjusting the position of the first valve.4. The method of claim 1 , wherein the second valve comprises a solenoid and wherein the positioning the at least one of the first valve and the second valve further comprises pulse width modulating the solenoid between an on state and an off state.5. The method of claim 4 , wherein ...

Apparatus and method for measuring clearance

Apparatus and methods for measuring clearance are disclosed. In one arrangement, a sensor is used to output a signal that is dependent on a separation between the component and the reference structure. A passage event integration comprising integrating an output from the sensor over at least a portion of a passage event of the component past the sensor is performed. Information about a clearance between the component and the reference structure is determined using a result of the passage event integration.

Method of gas turbine engine starting valve malfunction monitoring

FIELD: aviation. SUBSTANCE: invention relates to aircraft gas turbine engine starting circuit start-up valve malfunction monitoring method (200), including the following stages: gas turbine engine (100) starting (203), wherein a start command is sent to the start-up valve to open it; increasing (204) mode of gas turbine engine to the first predetermined threshold; during said increase (204) of gas turbine engine (100) mode: if detected (201) deviation between position sensors before gas turbine engine start-up phase or if deviation (205) is detected between position sensors, determination (207) of position sensor, switched between closed position and open position, wherein other position sensor remained in open or closed position; when first threshold is reached, memorizing (209) position sensor, switched between closed position and open position, as serviceable, and position sensor, left in open or closed position, as faulty, in order to measure the state of the start-up valve only based on the position of a good position sensor. Also disclosed are an aircraft gas turbine engine and a starting circuit. EFFECT: invention makes it possible to ensure safety of flights without spending additional means and without complicating operation of the aircraft. 10 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 736 228 C2 (51) МПК F01D 19/00 (2006.01) F02C 7/232 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 19/00 (2020.08); F02C 7/232 (2020.08) (21)(22) Заявка: 2019107759, 24.08.2017 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): САФРАН ЭРКРАФТ ЭНДЖИНЗ (FR) Дата регистрации: 12.11.2020 25.08.2016 FR 1657937 (43) Дата публикации заявки: 02.10.2020 Бюл. № 28 (45) Опубликовано: 12.11.2020 Бюл. № 32 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 25.03.2019 2 7 3 6 2 2 8 (56) Список документов, цитированных в отчете о поиске: FR 2972485 A1, 14.09.2012. FR 3012420 A1, ...

Method to control speed of turbine connected by generator to power supply system (versions) and device for implementing the method (versions)

FIELD: electrical engineering. SUBSTANCE: invention is designed to control speed of turbine. According to proposed method, high speeds of load changes in operation of turbine are detected, then at least one valve of turbine is throttled for a short time and turbine speed is controlled relative to new working load after change of load. Device for implementing the method contains actuating unit for short time throttling of at least one valve of turbine and computer unit to control speed of rotation after change of load by means of which at least two operating signals for setting turbine valve can be formed. First operating signal serves to open turbine valve and second one, to close turbine valve. EFFECT: improved reliability of power supply. 21 cl, 2 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2 298 653 (13) C2 (51) ÌÏÊ F01D 17/20 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2005102711/06, 30.06.2003 (72) Àâòîð(û): ÅÐÌÎØÊÈÍ Ãåííàäèé (RU), ÕÀÍÑ Êàðë (DE), ÊÐÛËΠÄìèòðèé (RU) (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 30.06.2003 (73) Ïàòåíòîîáëàäàòåëü(è): ÑÈÌÅÍÑ ÀÊÖÈÅÍÃÅÇÅËËÜØÀÔÒ (DE), ÂÑÅÐÎÑÑÈÉÑÊÈÉ ÍÀÓ×ÍÎÈÑÑËÅÄÎÂÀÒÅËÜÑÊÈÉ ÈÍÑÒÈÒÓÒ ÀÂÒÎÌÀÒÈÊÈ (RU) (43) Äàòà ïóáëèêàöèè çà âêè: 20.01.2006 (45) Îïóáëèêîâàíî: 10.05.2007 Áþë. ¹ 13 2 2 9 8 6 5 3 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: RU 2062330 Ñ1, 20.06.1996. RU 2016460 Ñ1, 15.07.1994. US 4258424 À, 24.03.1981. US 3340883 À, 12.09.1967. ÅÐ 0483570 À, 06.05.1992. US 4238924 A, 16.12.1980. DE 10055166 À, 23.05.2002. DE 1751821 À, 19.05.1971. SU 1038491 À, 30.08.1983. SU 1127981 A, 07.12.1984. 2 2 9 8 6 5 3 R U C 2 C 2 (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 04.02.2005 (86) Çà âêà PCT: DE 03/02169 (30.06.2003) (87) Ïóáëèêàöè PCT: WO 2004/005675 (15.01.2004) Àäðåñ äë ïåðåïèñêè: 103735, Ìîñêâà, óë. Èëüèíêà, 5/2, ÎÎÎ "Ñîþçïàòåíò", ïàò.ïîâ. Î.Ô.Èâàíîâîé (54) ÑÏÎÑÎÁ ÐÅÃÓËÈÐÎÂÀÍÈß ×ÀÑÒÎÒÛ ÂÐÀÙÅÍÈß ÒÓÐÁÈÍÛ, ...

Способ контроля неисправности пускового клапана газотурбинного двигателя

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2019 107 759 A (51) МПК F02C 7/268 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2019107759, 24.08.2017 (71) Заявитель(и): САФРАН ЭРКРАФТ ЭНДЖИНЗ (FR) Приоритет(ы): (30) Конвенционный приоритет: 25.08.2016 FR 1657937 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 25.03.2019 R U (43) Дата публикации заявки: 02.10.2020 Бюл. № 28 (72) Автор(ы): ВИДЕМАН, Адель Седрик Абир (FR), БОЙЕР, Давид, Жюльен (FR) (86) Заявка PCT: (87) Публикация заявки PCT: WO 2018/037193 (01.03.2018) R U (54) СПОСОБ КОНТРОЛЯ НЕИСПРАВНОСТИ ПУСКОВОГО КЛАПАНА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (57) Формула изобретения 1. Способ (200) контроля неисправности пускового клапана (13) контура (10) запуска авиационного газотурбинного двигателя (100), при этом указанный контур (10) запуска содержит стартер (11) и магистраль (12), выполненную с возможностью соединения с устройством подачи сжатого воздуха, при этом магистраль (12) содержит пусковой клапан (13), выполненный с возможностью изменять состояние между закрытым положением, в котором он перекрывает магистраль (12), и открытым положением, в котором он устанавливает сообщение между устройством подачи сжатого воздуха и стартером (11), при этом пусковой клапан (13) содержит два датчика (14, 15) положения, выполненные с возможностью переключаться между открытым положением, когда указанный пусковой клапан (13) находится в открытом положении, и закрытым положением, когда указанный пусковой клапан (13) находится в закрытом положении, при этом указанный способ содержит следующие этапы: запуск (203) газотурбинного двигателя (100), при этом в пусковой клапан (13) подают команду изменения состояния с целью его открывания; повышение (204) режима газотурбинного двигателя (100) до первого заранее определенного порога (S1); во время указанного повышения (204) режима газотурбинного двигателя (100): если обнаружено (201) отклонение между положениями датчиков (14 ...

Способ и устройство для регулирования частоты вращения турбины, подключенной посредством генератора к электрической сети энергоснабжения

ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2005 102 711 (13) A (51) ÌÏÊ F01L 1/00 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÇÀßÂÊÀ ÍÀ ÈÇÎÁÐÅÒÅÍÈÅ (21), (22) Çà âêà: 2005102711/06, 30.06.2003 (30) Ïðèîðèòåò: 04.07.2002 DE 10230125.5 (43) Äàòà ïóáëèêàöèè çà âêè: 20.01.2006 Áþë. ¹ 02 (86) Çà âêà PCT: DE 03/02169 (30.06.2003) (72) Àâòîð(û): ÅÐÌÎØÊÈÍ Ãåííàäèé (RU), ÕÀÍÑ Êàðë (DE), ÊÐÛËΠÄìèòðèé (RU) Àäðåñ äë ïåðåïèñêè: 103735, Ìîñêâà, óë. Èëüèíêà, 5/2, ÎÎÎ "Ñîþçïàòåíò", ïàò.ïîâ. Î.Ô.Èâàíîâîé R U Ôîðìóëà èçîáðåòåíè 1. Ñïîñîá ðåãóëèðîâàíè ÷àñòîòû âðàùåíè òóðáèíû (3), ïîäêëþ÷åííîé ïîñðåäñòâîì ãåíåðàòîðà (5) ê ýëåêòðè÷åñêîé ñåòè ýíåðãîñíàáæåíè , îòëè÷àþùèéñ òåì, ÷òî ïðåäóñìîòðåíû ñëåäóþùèå îïåðàöèè: a) âî âðåì ðàáîòû òóðáèíû (3) íåïðåðûâíî îïðåäåë þò, èìååò ëè ìåñòî èçìåíåíèå íàãðóçêè òóðáèíû (3), b) â ñëó÷àå, åñëè êîíñòàòèðóþò èçìåíåíèå íàãðóçêè, îïðåäåë þò ñêîðîñòü (10) ýòîãî èçìåíåíè íàãðóçêè, c) â ñëó÷àå, åñëè ñêîðîñòü (10) èçìåíåíè íàãðóçêè ïî ìîäóëþ áîëüøå, ÷åì çàðàíåå óñòàíîâëåííà ìàêñèìàëüíà ñêîðîñòü (13) èçìåíåíè íàãðóçêè è èçìåíåíèå íàãðóçêè ïðîèñõîäèò â íàïðàâëåíèè ìåíüøåé íàãðóçêè, òî ïîñðåäñòâîì èñïîëíèòåëüíîãî âîçäåéñòâè , ïî ìåíüøåé ìåðå, îäèí êëàïàí (15) òóðáèíû êðàòêîâðåìåííî ïðèâîä ò â äåéñòâèå â íàïðàâëåíèè åãî ïîëîæåíè çàêðûòè è ïðè ýòîì êðàòêîâðåìåííî çàêðûâàþò, ïî ìåíüøåé ìåðå, îäèí êëàïàí (15) òóðáèíû, è d) ÷àñòîòó âðàùåíè òóðáèíû (3) îòíîñèòåëüíî òåêóùåé ðàáî÷åé íàãðóçêè, êîòîðà ïîëó÷àåòñ ïîñëå èçìåíåíè íàãðóçêè, ðåãóëèðóþò ïîñðåäñòâîì ðåãóëèðóþùåãî âîçäåéñòâè íà, ïî ìåíüøåé ìåðå, îäèí êëàïàí (15) òóðáèíû. 2. Ñïîñîá ïî ï.1, îòëè÷àþùèéñ òåì, ÷òî ðåãóëèðóþùåå âîçäåéñòâèå íà, ïî ìåíüøåé ìåðå, îäèí êëàïàí (15) òóðáèíû îêàçûâàþò ïîñðåäñòâîì, ïî ìåíüøåé ìåðå, äâóõ èñïîëíèòåëüíûõ ñèãíàëîâ (19, 21), ïðè÷åì ïîñðåäñòâîì ïåðâîãî èñïîëíèòåëüíîãî ñèãíàëà (19) èç, ïî ìåíüøåé ìåðå, äâóõ èñïîëíèòåëüíûõ ñèãíàëîâ äîñòèãàåòñ ïðèâåäåíèå â Ñòðàíèöà: 1 RU A 2 0 0 5 1 0 2 7 1 1 A (54) ÑÏÎÑÎÁ È ÓÑÒÐÎÉÑÒÂÎ ÄËß ÐÅÃÓËÈÐÎÂÀÍÈß ...

Patent RU2019107759A3

ВИ“? 2019107759” АЗ Дата публикации: 26.10.2020 Форма № 18 ИЗ,ПМ-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 2019107759/12(015034) 24.08.2017 РСТ/ЕК2017/052272 24.08.2017 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. 1657937 25.08.2016 ЕК Название изобретения (полезной модели): [Х] - как заявлено; [ ] - уточненное (см. Примечания) СПОСОБ КОНТРОЛЯ НЕИСПРАВНОСТИ ПУСКОВОГО КЛАПАНА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ Заявитель: САФРАН ЭРКРАФТ ЭНДЖИНЗ, ЕВ 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) ЕОТО 19/00 (2006.01) Е02С 7/232 (2006.01) 5. ОБЛАСТЬ ПОИСКА 5.1 Проверенный минимум документации РСТ (указывается индексами МПК) В64р 37/32; [ОТО 19/00; Е02С 7/232; С06Е 11/00. 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): СМГРА, РЕРАТБЗ пе, ЕВЗСО, Езрасепев, Соозе, ]-Р]а Рас, КТРК $, РАТЕМТЗСОРЕ, Раб еагсв, Оцез{е]-Огри, КОРТО, ИЗРТО 6. ДОКУМЕНТЫ, ОТНОСЯЩИЕСЯ К ПРЕДМЕТУ ПОИСКА Кате- Наименование ...

MEASURING DEVICE FOR REGISTRATION OF THE ROTARY PULSE OF THE ENGINE ROTOR, AND ALSO A WAY FOR THIS

1. Измерительное устройство (1) для регистрации вращательного движения ротора (10), который установлен, прежде всего, с возможностью вращения в корпусе (17) компрессора реактивного двигателя, ! при этом ротор имеет лопастные элементы (13), расположенные по периметру на предпочтительно одинаковом расстоянии друг от друга, и ! при этом, кроме того, предусмотрен по меньшей мере один датчик (11), а на роторе (10) выполнена по меньшей мере одна мера, которая посредством вращательного движения является периодически регистрируемой датчиком (11), ! отличающееся тем, что указанная мера образована по меньшей мере одним модифицированным лопастным элементом (14), который укорочен в области (15) вершины лопасти, и при этом датчик (11) при прохождении мимо него лопастных элементов (13) выдает в каждом случае одинаковый измерительный сигнал, а при прохождении мимо него модифицированного лопастного элемента (14) выдает модифицированный измерительный сигнал (16). ! 2. Измерительное устройство (1) по п.1, отличающееся тем, что датчик (11) выполнен в виде чувствительного к расстоянию датчика (11). ! 3. Измерительное устройство (1) по п.2, отличающееся тем, что датчик (11) выполнен в виде емкостного, магнитного и/или оптического датчика. ! 4. Измерительное устройство (1) по п.3, отличающееся тем, что датчик (11) расположен в корпусе (17) компрессора реактивного двигателя для того, чтобы находиться вблизи внешней траектории лопастных элементов (13, 14). ! 5. Измерительное устройство (1) по п.4, отличающееся тем, что укороченная область (15) модифицированного лопастного элемента (14) простирается по всей длине хорды модифицированного лопастного элемента (14) или выполнена только на РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2009 109 151 (13) A (51) МПК G01P 3/481 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21), (22) Заявка: 2009109151/28, 01.09.2007 (71) Заявитель(и): МТУ АЭРО ЭНДЖИНС ГМБХ (DE) (30) Конвенционный приоритет ...

Method and device for regulating the rotational speed of a turbine connected to an electric power supply mains by means of a generator

按照本发明的方法规定，在透平(3)运行期间检测过大的负荷改变速度(10)，对透平(3)的至少一个透平阀(15)短时节流，以及最后在负荷变化后根据新的运行负荷调节透平(5)的转速。一按本发明的装置(1)用于实施该方法，该装置包括用于短时节流所述至少一个透平阀(15)的调节单元(11)，以及用于按照负荷改变调节转速的计算单元(17)，借助该计算单元可产生至少两个调节透平阀(15)用的调节信号(19、21)。在这里，第一个调节信号(19)用于朝其开启方向操纵该透平阀(15)，以及第二个调节信号(21)用于朝其关闭方向操纵该透平阀(15)。

Integrated steam / air cooler for gas turbine and method of operating a cooler for gas turbine

Method and apparatus for controlling steam turbine inlet flow to limit shell and rotor thermal stress

터빈 로터를 갖는 증기 터빈을 통과하는 증기 유동을 제어하는 방법에 있어서, 터빈 로터에서의 열응력을 계산한 것을 근거로 최대 열전달률(18)이 결정된다. 최대 열전달률을 근거로 최대 증기 유량(20)이 계산될 수 있다. 증기 터빈을 통과하는 실제 증기 유량이 결정되고, 실제 증기 유량과 최대 증기 유량 사이의 차이를 근거로 터빈 흡입 밸브(28)가 제어된다. 이러한 방법에서는, 시동 시간을 최소화하고 가동성을 최대화하면서 열응력을 허용 가능 수준으로 제한하는 방식으로, 증기 터빈으로의 증기 유동이 제어될 수 있다. In the method of controlling the steam flow through a steam turbine having a turbine rotor, the maximum heat transfer rate 18 is determined based on the calculation of the thermal stress in the turbine rotor. The maximum steam flow rate 20 can be calculated based on the maximum heat transfer rate. The actual steam flow rate through the steam turbine is determined, and the turbine intake valve 28 is controlled based on the difference between the actual steam flow rate and the maximum steam flow rate. In this method, the steam flow to the steam turbine can be controlled in a manner that limits thermal stress to an acceptable level while minimizing start-up time and maximizing operability.

The method being modeled to compressor speed

本发明涉及一种对涡轮增压器的压缩机速度进行建模的方法，其包括以下步骤：确定压缩机两端的温度差，确定流过压缩机的质量流量，以及，计算作为压缩机两端的温度差和所述质量流量的函数的压缩机速度值。

Device and method of protection of turbomachine calculator in aircraft from speed measurement errors

FIELD: measuring equipment.SUBSTANCE: protection device of an aircraft turbomachine calculator from speed measurement errors, containing in the adjustment channel a speed sensor for the turbomachine gearbox shaft, the first speed measurement circuit and speed adjustment circuit. In the adjustment channel the device contains a speed sensor for the turbomachine gas generator shaft, the second speed measurement circuit and turbomachine shutdown control circuit. Both speed sensors are two sensors, which are installed opposite two phonic wheels of different processes and having a different number of teeth. The first and second speed adjustment circuits compare a frequency signal with a minimum threshold and deliver the first and second speed issue detection signals, when the measured frequency is lower than the minimum threshold. The device additionally includes a cross-check circuit of the first and second speeds, obtained from the first and second speed measurement circuits, respectively. The cross-check circuit delivers the third speed issue detection signal in case of an abnormal deviation between the first and second speeds. The frequency signals are various frequency signals. According to the method of protection of the turbomachine calculator two pseudo-sinusoidal frequency signal, the frequency signals with a minimum threshold are compared and the speed issue detection signals are delivered, the speeds, delivered from the speed adjustment channel and control channel, are cross-checked, and the third speed issue detection signal is delivered, the machine shutdown is controlled in case of a speed issue.EFFECT: improvement of the device.11 cl, 2 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 641 329 C2 (51) МПК F01D 17/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 17/00 (2006.01); F01D 17/06 (2006.01) (21)(22) Заявка: 2015122453, 12.11.2013 (24) Дата начала отсчета срока действия патента: (73) ...

Apparatus for testing low-speed, high-speed and over-speed by using power generation turbine

A testing device for low speed, high speed, and over speed of a power plant turbine is provided to reduce cost of maintaining the turbine by performing a test using pulse value of a pulse generation unit without operating the turbine at high speed. A testing device(200) for low speed, high speed, and over speed of a power plant turbine comprises the followings: a pulse generation unit(210) outputting rated pulse value corresponding to a rated rotation speed of the turbine; a fuel control unit(140) transmitting a pulse generation decrease signal or a pulse generation increase signal to the pulse generation unit; and a control unit(220) receiving the rated pulse value, transmitting a fuel decrease signal or a fuel increase signal to the fuel control unit, receiving altered pulse value from the pulse generation unit, calculating an altered rotation speed corresponding to the altered pulse value, and if the altered rotation speed reduces or increases as the preset rotation speed, blocking the fuel decrease or increase signal and controlling to keep the rotation speed, or operating an emergency stop system.

TURBOCHARGER SPEED SENSOR INSERT WITH POSITION OF BEARING SPACING BUSH

1. Корпус подшипников турбонагнетателя, содержащийканал подшипников;два радиальных подшипника, расположенных в канале подшипников;трубчатую распорную втулку подшипников, имеющую первый и второй концы относительно направления оси, предназначенную для разнесения указанных радиальных подшипников и имеющую по меньшей мере одно радиально расположенное отверстие;установочный канал;имеющий в целом трубчатую форму вкладыш, установленный в установочный канал и выступающий в отверстие в распорной втулке подшипников;датчик оборотов, установленный в трубчатый вкладыш с использованием резьбового соединения или посадки с натягом.2. Турбонагнетатель по п. 1, отличающийся тем, что имеющий в целом трубчатую форму вкладыш установлен в установочный канал с использованием резьбового соединения, посадки с натягом, запрессовки, клеевого, шипового или сварного соединения.3. Турбонагнетатель по п. 1, отличающийся тем, что трубчатый вкладыш и датчик оборотов имеют контрольные элементы, определяющие глубину вхождения датчика оборотов.4. Турбонагнетатель по п. 1, отличающийся тем, что вкладыш имеет внутреннюю резьбу и наружную резьбу.5. Турбонагнетатель по п. 1, отличающийся тем, что корпус подшипников имеет наружную поверхность, трубчатый вкладыш содержит сегмент, выступающий наружу за пределы наружной поверхности корпуса подшипников, и при этом указанный выступающий сегмент содержит элементы конструкции, предназначенные для зацепления указанного вкладыша с целью его вращения.6. Турбонагнетатель по п. 5, отличающийся тем, что указанные элементы конструкции для зацепления указанного вкладыша с целью его вращения содержат одну или несколько РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (51) МПК F02B 39/00 (11) (13) 2015 107 165 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015107165, 31.07.2013 (71) Заявитель(и): БОРГВАРНЕР ИНК. (US) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): ЧЕКАНСКИЙ, Джейсон В. (US) 17.08.2012 US 61/684,280 (85) ...

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

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

Modular and autonomous assembly for detecting the angular position of the blades of an impeller and modular and autonomous assembly for detecting damage to the blades of an impeller of a turbine engine

A modular and autonomous assembly (1) for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly (1) comprising: - at least one electrical power source (711b, 71b, 72b) enabling the elements of the detection assembly (1) to operate independently of the turbine engine on which it is intended to be mounted, - at least one first sensor (71) intended to be associated with the first impeller, - at least one second sensor (72) intended to be associated with the second impeller, and - a main housing (711) comprising a processing unit (711e) and storage means (711c).

Detecting damage to a gas turbine engine

A computer implemented method (1100) for detecting a damage to a gas turbine engine (10). The gas turbine engine (10) includes a fan (402) and a plurality of turbine stages including a low pressure turbine stage (406). The fan (402) is drivably coupled to the low pressure turbine stage (406). The method (1100) includes receiving (1102) a first signal (S1) indicative of a speed of rotation (N1) of the fan (402). The method (1100) further includes receiving (1104) a second signal (S2) indicative of a speed of rotation (N1T) of the low pressure turbine stage (406). The method (1100) further includes determining (1106) a difference metric (ΔN) representative of a difference between the speed of rotation (N1) of the fan (402) and the speed of rotation (N1T) of the low pressure turbine stage (406). The method (1100) further includes determining (1108) whether a damage event has occurred based on whether the difference metric (ΔN) passes a threshold (TH).

Measurement of the rotational speed of a hollow shaft of a turbomachine

Turbine rotor assembly having a retaining collar for a bayonet mount

A retaining collar is disclosed for a bayonet mount comprising a rotor disc having a male mounting member defining a pair of apertures and an auxiliary annular wheel defining a plurality of mounting slots. The retaining collar comprises a ring-shaped body and a pair of retention pins. The ring-shaped body has a pair of circumferential end portions separated by a circumferential gap, and an arcuate radial outer surface extending circumferentially between the end portions. The body is dimensioned so that the radial outer surface frictionally engages a radial inner surface of a cylindrical male mounting member in the bayonet mount. The pair of retention pins each extend radially outward from one of the circumferential end portions. Each of the retention pins are dimensioned to extend radially outward from the body through one of said apertures and one of said mounting slots.

Turbine assembly with auxiliary wheel

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Turbine assembly with auxiliary wheel

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Detecting damage to a gas turbine engine

A computer implemented method for detecting a damage to a gas turbine engine. The gas turbine engine includes a fan and a plurality of turbine stages including a low pressure turbine stage. The fan is drivably coupled to the low pressure turbine stage. The method includes receiving a first signal indicative of a speed of rotation of the fan. The method further includes receiving a second signal indicative of a speed of rotation of the low pressure turbine stage. The method further includes determining a difference metric representative of a difference between the speed of rotation of the fan and the speed of rotation of the low pressure turbine stage. The method further includes determining whether a damage event has occurred based on whether the difference metric passes a threshold.

An apparatus and method for detecting a damaged rotary machine aerofoil

A gas turbine engine (10) comprises a fan rotor (26) having a plurality of fan blades (24) and an apparatus (34) for detecting damage to the fan blades (24). The apparatus (34) comprises a transducer (36) arranged to detect the pressure in the gas flow around the fan blades (34) and to produce a pressure signal. A speed sensor (48) is arranged to measure the speed of rotation of the fan rotor (26) and to produce a speed signal. A processor unit (40) analyses the pressure signal and the speed signal to detect changes in the amplitude of the pressure signal, which occur at multiples of the rotational frequency of the fan rotor (24). The changes indicate differences in pressure between the gas flow around a damaged fan blade (24) and the gas flow around the remainder of the fan blades (24). The processor unit (40) sends a signal indicative of damage to a fan blade (24), if the difference in pressure is above the predetermined level, to an indicator device (44,46).

Shaft monitoring system

本公开题为“轴监测系统”，提供了一种用于监测旋转轴的轴向位置的监测系统。该系统包括音轮（56），该音轮与轴（54,62）同轴安装以随该轴旋转。音轮包括周向齿排。该系统还包括传感器（60），该传感器被配置为通过生成交替测量信号来检测齿排的通过。齿围绕排配置，使得齿对该交替测量信号贡献分量。齿沿轮（56）的轴向方向渐缩，并且传感器（60）相对于音轮被定位成使得在使用中轴（54,62）的轴向位移导致由传感器生成的信号改变分量的振幅和脉冲宽度中的一者或两者，从而可监测轴的该轴向位置。

Control system and method

Disclosed are apparatus and methods for controlling parameters of fluid-driven systems. A control unit of the invention compares an input control signal to a tachometer signal from a fluid-driven turbine to produce a flow signal for controlling the turbine speed. The speeds of turbines in series are linked by the tachometer signal of the first turbine acting as the control signal for the following turbines. A critical speed interval is identified in relation to a range of values of the control signal. As the speed of a turbine is increased or decreased, its control unit holds the turbine speed at the limit of the critical speed interval, then rapidly accelerates the turbine through the interval to avoid prolonged operation at the turbine's critical speed. The individual critical speeds of separate turbines in series may be accommodated by critical speed intervals defined in separate control units for each of the turbines. Multiple critical speeds for a given turbine may also be provided for by defining multiple critical speed intervals within the corresponding control unit.

Disassembly method for gas turbines and calibration device

Turbine valve controller

Abstract of the Disclosure A turbine control device which compensates for non-linearity of the degree-of-opening/flow-rate characteristic of a regulating valve. The device has a turbine rotation speed detector, a calculator to determine a desired flow rate based on a pre-determined rotation speed and the detected speed, a valve for controlling the flow rate with a variable degree of opening, a flow rate detector, a memory unit for memorizing combinations of the detected flow rate and respective degrees of opening of the valve, a converter for converting the desired flow rate into a valve opening command signal based on the memorized combinations of the flow rate and respective degrees of opening of the valve, and a servo controller for the valve.

Modular and autonomous assembly for detecting the angular position of the blades of a paddle wheel and modular and autonomous assembly for detecting damage to the blades of a turbine engine impeller

Ensemble modulaire et autonome de détection de la position angulaire des aubes d’une roue à aubes et ensemble modulaire et autonome de détection d’endommagement des aubes d’une roue à aubes d’une turbomachine Un ensemble (1) modulaire et autonome de détection de la position angulaire des aubes d’une roue à aubes destiné à être monté sur une turbomachine, l’ensemble (1) comprend au moins une source d’alimentation électrique (711b, 71b, 72b) permettant le fonctionnement des éléments de l’ensemble de détection (1) indépendamment de la turbomachine sur laquelle il est destiné à être embarqué, au moins un premier capteur (71) destiné à être associé à la première roue à aubes, au moins un second capteur (72) destiné à être associé à la seconde roue à aubes, et un boîtier principal (711) comportant une unité de traitement (711e) et des moyens de mémorisation (711c). Figure pour l’abrégé : Fig. 1. Modular and autonomous assembly for detecting the angular position of the blades of a blade wheel and modular and autonomous assembly for detecting damage to the blades of a blade wheel of a turbomachine A modular and autonomous assembly (1) for detecting of the angular position of the blades of a bladed wheel intended to be mounted on a turbine engine, the assembly (1) comprises at least one electrical power source (711b, 71b, 72b) allowing the operation of the elements of the detection assembly (1) independently of the turbine engine on which it is intended to be installed, at least one first sensor (71) intended to be associated with the first blade wheel, at least one second sensor (72) intended to be associated to the second paddle wheel, and a main housing (711) comprising a processing unit (711e) and storage means (711c). Figure for abstract: Fig. 1.

PRESSURIZATION VALVE WITH TWO VALVES

Un clapet (24) à soupape double (29, 30) est raccordé à un réservoir de fluide (3) et un équipement (8) pouvant recevoir une petite quantité de trop-plein essentiellement à l'état gazeux du réservoir (3). Cela se produit quand la soupape primaire (29) est ouverte. En cas de trop-plein plus important et essentiellement à l'état liquide, on réalise une commutation d'ouvertures (36, 39 et 37, 38, 42) pour évacuer le trop-plein vers une autre branche d'exutoire du clapet (24), sans le faire parvenir à l'équipement (8). L'invention peut trouver l'utilité dans un circuit de lubrification à l'huile, où une hypothétique fuite de carburant dans l'huile peut amener le réservoir d'huile à déborder dans le clapet (24) et où un écoulement significatif de liquide vers l'équipement (8) doit être évité; l'huile sortant par l'autre branche de l'exutoire peut séjourner dans un réservoir muni d'un système de vidange. A valve (24) with double valve (29, 30) is connected to a fluid reservoir (3) and equipment (8) capable of receiving a small amount of overflow essentially in the gaseous state of the reservoir (3). This occurs when the primary valve (29) is open. In the event of a larger overflow and essentially in the liquid state, switching openings (36, 39 and 37, 38, 42) is carried out in order to discharge the overflow to another branch of the valve outlet ( 24), without sending it to the equipment (8). The invention can find utility in an oil lubrication circuit, where a hypothetical fuel leak in the oil can cause the oil tank to overflow in the valve (24) and where a significant flow of liquid towards the equipment (8) should be avoided; the oil leaving through the other branch of the outlet can remain in a tank provided with a draining system.

Turbine assembly with auxiliary wheel

Various embodiments of the present application provide one or more of; (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Device for determination of rotation frequency of machine rotating part with redundant detectors and evaluation circuits

FIELD: physics, measurement. SUBSTANCE: invention is related to the field of metering equipment and may be used to monitor rotation frequency of turbine impeller. In device according to invention, two parallel subdevices are provided, which have three signal inputs to obtain redundant registration of two out of three signals of rotation frequency. Every subdevice comprises calculating unit used to calculate rotation frequency of machine rotating part. Besides every subdevice has signal input for generation of rotation frequency calculated by appropriate computing unit. Corresponding signal inputs of subdevices are loaded parallel to output signals of rotation frequency detector. In case of error device function, according to invention, may fully be taken by one of subdevices so that both erroneous output signal of rotation frequency detector and failure of one subdevice are permitted. EFFECT: higher reliability of control. 23 cl, 2 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß RU (19) (11) 2 350 968 (13) C2 (51) ÌÏÊ G01P 3/489 (2006.01) G05B 9/03 (2006.01) G06F 11/20 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2005102712/28, 30.06.2003 (72) Àâòîð(û): ÅÐÌÎØÊÈÍ Ãåííàäèé (RU), ÕÀÍÑ Êàðë (DE), ÊÐÛËΠÄìèòðèé (RU) (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 30.06.2003 (43) Äàòà ïóáëèêàöèè çà âêè: 20.01.2006 (45) Îïóáëèêîâàíî: 27.03.2009 Áþë. ¹ 9 (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 04.02.2005 2 3 5 0 9 6 8 R U (87) Ïóáëèêàöè PCT: WO 2004/005938 (15.01.2004) C 2 C 2 (86) Çà âêà PCT: DE 03/02170 (30.06.2003) Àäðåñ äë ïåðåïèñêè: 103735, Ìîñêâà, óë.Èëüèíêà, 5/2, ÎÎÎ "Ñîþçïàòåíò", ïàò.ïîâ. Ì.Í. Ñòðó÷êîâó, ðåã.¹ 1102 (54) ÓÑÒÐÎÉÑÒÂÎ ÄËß ÎÏÐÅÄÅËÅÍÈß ×ÀÑÒÎÒÛ ÂÐÀÙÅÍÈß ÂÐÀÙÀÞÙÅÉÑß ÄÅÒÀËÈ ÌÀØÈÍÛ Ñ ÈÇÁÛÒÎ×ÍÛÌÈ ÄÀÒ×ÈÊÀÌÈ È ÑÕÅÌÀÌÈ ÎÖÅÍÊÈ (57) Ðåôåðàò: Èçîáðåòåíèå îòíîñèòñ ê îáëàñòè èçìåðèòåëüíîé òåõíèêè è ìîæåò áûòü èñïîëüçîâàíî äë êîíòðîë ÷àñòîòû âðàùåíè ðàáî÷åãî êîëåñà òóðáèíû.  ...

DEVICE AND METHOD FOR PROTECTING AN AIRCRAFT TURBO-MACHINE COMPUTER AGAINST SPEED MEASUREMENT ERRORS

PRESSURIZATION VALVE WITH TWO VALVES

Un clapet (24) à soupape double (29, 30) est raccordé à un réservoir de fluide (3) et un équipement (8) pouvant recevoir une petite quantité de trop-plein essentiellement à l'état gazeux du réservoir (3). Cela se produit quand la soupape primaire (29) est ouverte. En cas de trop-plein plus important et essentiellement à l'état liquide, on réalise une commutation d'ouvertures (36, 39 et 37, 38, 42) pour évacuer le trop-plein vers une autre branche d'exutoire du clapet (24), sans le faire parvenir à l'équipement (8). L'invention peut trouver l'utilité dans un circuit de lubrification à l'huile, où une hypothétique fuite de carburant dans l'huile peut amener le réservoir d'huile à déborder dans le clapet (24) et où un écoulement significatif de liquide vers l'équipement (8) doit être évité; l'huile sortant par l'autre branche de l'exutoire peut séjourner dans un réservoir muni d'un système de vidange.

Patent FR2727809B1

METHOD FOR MEASURING THE DEFORMATION OF A TURBOMACHINE BLADE DURING THE OPERATION OF THE TURBOMACHINE

Une méthode de mesure de la déformation d'une aube de turbomachine (1) comportant : - une étape de positionnement d'au moins un accéléromètre (A) sur un point local de l'aube de turbomachine (1) ; - une première étape de mesure (Gx) de la force centrifuge (G), par l'accéléromètre (A), au point local de l'aube de turbomachine (1) selon la direction de mesure donnée (X) à une première vitesse prédéterminée (V) ; une deuxième étape de mesure (Gx') de la force centrifuge (G') à une deuxième vitesse prédéterminée (V') ; - une étape de détermination du déplacement angulaire (alpha ) de la direction de mesure (X, X') de l'accéléromètre (A, A') par rapport à la direction centrifuge (G, G') en fonction de la première mesure d'accélération (Gx) et de la deuxième mesure d'accélération (Gx'), ledit déplacement angulaire (ax) correspondant à une déformation angulaire du point local de l'aube de turbomachine (1).

Patent FR2175381A5

ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH A SPEED REDUCER DRIVEN BLOWER, THE ASSEMBLY COMPRISING A PRESSURE REGULATED OIL FILM COMPRESSION DAMPER

L’invention concerne un ensemble (30) pour turbomachine d’aéronef comprenant une soufflante (15) entraînée par un réducteur de vitesse (20), l’ensemble comprenant : - un palier (22) de guidage d’un arbre (13), comprenant une bague extérieure (34) ; - un amortisseur (46) à compression de film d’huile, comprenant un espace annulaire (48) délimité radialement entre une surface extérieure (35) d’une bague extérieure (34) de palier, et une surface intérieure de logement (44) prévue sur un élément de stator (38) ; et - un circuit (62) d’alimentation en huile, comprenant un premier conduit (80) d’alimentation en huile de l’espace annulaire (48) de l’amortisseur, le circuit comportant un moyen (76) de mise en pression de l’huile, et, entre le moyen (76) et le premier conduit (80), un régulateur (78) de pression de l’huile. Figure pour l’abrégé : Figure 2. The invention relates to an assembly (30) for an aircraft turbine engine comprising a fan (15) driven by a speed reducer (20), the assembly comprising: - a bearing (22) for guiding a shaft (13) , comprising an outer ring (34); - an oil film compression damper (46), comprising an annular space (48) delimited radially between an outer surface (35) of an outer ring (34) of the bearing, and an inner housing surface (44) provided on a stator element (38); and - an oil supply circuit (62), comprising a first duct (80) for supplying oil to the annular space (48) of the shock absorber, the circuit comprising means (76) for pressurizing oil, and, between the means (76) and the first conduit (80), an oil pressure regulator (78). Figure for abstract: Figure 2.