УСТРОЙСТВО СЛИВА ТЕКУЧИХ СРЕД ДЛЯ АВИАЦИОННОГО ДВИГАТЕЛЯ

Устройство слива текучих сред для авиационного двигателя, содержащее коллектор, выполненный с возможностью сбора текучих сред, сливаемых из двигателя, содержащее средства откачки текучих сред, содержащихся в коллекторе, и удаления этих текучих сред, и средства контроля, выполненные с возможностью оповещения о ненормальном сборе текучих сред коллектором, причем эти средства контроля выполнены с возможностью активации, когда расход собираемых текучих сред превышает пропускную способность средств откачки. Описаны также авиационный двигатель, содержащий данное устройство слива, и способ контроля такого авиационного двигателя. Технический результат изобретения – повышение эффективности слива текучих сред авиационного двигателя. 3 н. и 7 з.п. ф-лы, 10 ил.

TEMPERATURANZEIGENDE FARBE UND VERFAHREN ZUR HERSTELLUNG EINER PROBE HIERMIT

Motorpumpenaggregat

Aufgabe: Das Motorpumpenaggregat enthält einen Elektromotor (2), eine Pumpe (3), ein durch einen Elektromagneten (25) betätigtes Ventil (4) und einen Drucksensor (5). Der Konflikt zwischen den regelungstechnischen Anforderungen für den Drucksensor und den Anforderungen der Leitungsführung soll ohne Kompromisse auf der Seite der Regelungstechnik bei vertretbaren Herstellkosten, hoher Zuverlässigkeit und günstiger Montage der Komponenten gelöst werden Lösung: Der Drucksensor (5) ist räumlich zwischen dem Auslass (11) der Pumpe (3) und dem Einlass (12) des Ventils (4) angeordnet, wobei die elektrische Verbindung des Drucksensors (5) mit der Steckverbindung (13) über drei elektrische Leitungszüge (18, 18', 18'') erfolgt, die gegen das Arbeitsfluid abgedichtet sind und mit drei Federn (14, 14', 14'') versehen sind, die mittelbar oder unmittelbar auf die Kontaktstifte (10, 10', 10'') des Drucksensors (5) drücken Anwendung: Motorpumpenaggregate der beschriebenen Art werden in Fahrzeuggetrieben ...

A transducer mount and a transducer assembly incorporating such a mount

A transducer assembly 100 for connecting a transducer 102 to a device, the transducer assembly comprising: a transducer mount 110 adapted to receive the transducer; and a clamp 120 comprising first and second jaws 122, 124, the first and second jaws being adapted to selectively clamp to a flange portion 106 of the device. The transducer mount 110 may comprise a housing 112, a resilient member 114 and first and second end walls 115, 116. The first end wall may be operatively connected to the device. The transducer 102 may be held within the housing 112 and adjacent to the first end wall 115, the resilient member 114 being disposed between the transducer 102 and the second end wall 116.

Sensor system for a pump impeller assembly

OIL MONITORING

The oil quality in an oil reservoir of a pump is monitored using the disclosed oil-monitoring sensor. The oil-monitoring sensor includes a first capacitive portion for measuring oil level and a second capacitive portion for measuring dielectric constant of the oil. Changes in dielectric constant of the oil are indicative of degradation of the quality of the oil (e.g., due to contaminants, oxidation, etc.) So oil-monitoring sensor is used to indicate various parameters about the oil quality to an operator. Using the disclosed sensors, the quality of the lubricant and/or cooling oil used by the pump may be monitored without needing to be present at the pump, or without needing to access the interior of the pump (or oil reservoir).

TURBOMACHINES WITH SAW OR BAW DEVICES, MEASURING ARRANGEMENTS AND INSTALLATION METHODS

An arrangement is disclosed for measuring an environment parameter at a rotor of a rotary machine; according to some embodiments, the parameter to be measured is temperature and the machine to monitor is a turbomachine. The arrangement includes at least: a SAW or BAW device (512) electrically coupled with an antenna (520), a parameter-sensitive impedance device (532), and two identical cables (542, 544) electrically coupling the SAW or BAW device (512) respectively with the impedance device (532) and a short-circuit (550) or an open-circuit or a matching impedance device. The SAW or BAW device (512) is located in a first zone of the rotor, while the parameter-sensitive impedance device (532) is located in a second zone of the rotor remote from the first zone of the rotor. An interrogator can obtain environment parameter values by sending RF signals to the SAW or BAW device (512) through the antenna (520).

SHAFT SHEAR DETECTION THROUGH SHAFT OSCILLATION

There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed, the oscillation wave having a wave modulation frequency and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature.

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 eine Messmatrix auf der Basis mehrerer erster Resonanzfrequenz-Delta-Ankunftszeitvektoren, die einer Laufschaufel und einer ersten Sensorvorrichtung entsprechen, und mehrerer zweiter Resonanzfrequenz-Delta-Ankunftszeitvektoren generiert (709), der Laufschaufel und einer zweiten Sensorvorrichtung entsprechen, eine Resonanzmatrix auf der Basis der Messmatrix derart generiert (708), dass Einträge in der Resonanzmatrix im Wesentlichen linear unkorreliert und linear unabhängig sind, und ein Resonanzsignal unter Verwendung eines ersten Teilsatzes der Einträge der Resonanzmatrix generiert (712), wobei das Resonanzsignal im Wesentlichen gemeinsame Beobachtungen und Komponenten der mehreren ersten Resonanzfrequenz-Delta-Ankunftszeitvektoren und der mehreren zweiten Resonanzfrequenz-Delta-Ankunftszeitvektoren aufweist.

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 eine Messmatrix auf der Basis mehrerer erster Resonanzfrequenz-Delta-Ankunftszeitvektoren, die einer Laufschaufel und einer ersten Sensorvorrichtung entsprechen, und mehrerer zweiter Resonanzfrequenz-Delta-Ankunftszeitvektoren generiert (709), der Laufschaufel und einer zweiten Sensorvorrichtung entsprechen, eine Resonanzmatrix auf der Basis der Messmatrix derart generiert (708), dass Einträge in der Resonanzmatrix im Wesentlichen linear unkorreliert und linear unabhängig sind, und ein Resonanzsignal unter Verwendung eines ersten Teilsatzes der Einträge der Resonanzmatrix generiert (712), wobei das Resonanzsignal im Wesentlichen gemeinsame Beobachtungen und Komponenten der mehreren ersten Resonanzfrequenz-Delta-Ankunftszeitvektoren und der mehreren zweiten Resonanzfrequenz-Delta-Ankunftszeitvektoren aufweist.

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

FLUID DRAINAGE DEVICE FOR AN AIRCRAFT ENGINE

TURBOMACHINE AND CONTROL METHOD

L'invention concerne le domaine des turbomachines, et plus spécifiquement un procédé de régulation d'au moins une telle turbomachine (5) qui comprend un compresseur (8), une chambre de combustion (9), une première et une deuxième turbines (10,12) en aval de la chambre de combustion, un premier arbre rotatif (11) solidaire en rotation au moins dudit compresseur et de ladite première turbine, un deuxième arbre rotatif (13) duquel la deuxième turbine est solidaire en rotation, ce deuxième arbre rotatif étant toutefois libre en rotation par rapport au premier arbre rotatif, et un régulateur (15) pour piloter l'alimentation de la chambre de combustion en carburant. Ledit régulateur coupe l'alimentation de la chambre de combustion en carburant si une vitesse de rotation (N2) dudit deuxième arbre rotatif dépasse un seuil maximal (N2,max) qui varie en fonction d'au moins un paramètre physique indicatif associé à une puissance mécanique extraite à des gaz de combustion à la deuxième turbine.

Apparatus and method for measuring turbine temperature

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

Systems and methods for sensors on circumferential interior surface of turbomachine casing

A casing for a turbomachine is disclosed. The casing includes a casing body including an interior surface and an exterior surface. At least one sensor is coupled relative to the interior surface of the body, the at least one sensor at most only partially extending through the body. A communications lead is operatively coupled to the at least one sensor, and extends circumferentially along the interior surface of the body.

System and method for locating a probe within a gas turbine engine

A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also include determining a current location of the probe tip within the engine based at least in part on the location-related signals and identifying a virtual location of the probe tip within a three-dimensional model of the engine corresponding to the current location of the probe tip within the engine. Moreover, the method may include providing for display the three-dimensional model of the engine, wherein the virtual location of the probe tip is displayed as a visual indicator within the three-dimensional model.

AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE

Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

APPARATUS AND METHOD FOR MEASURING TURBINE TEMPERATURE

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

Turbomachinery heat transfer system

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

Method and apparatus for cooling turbine blades

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE

ENGINE INLET COVER DETECTION SYSTEM

The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, a second sensor, an engine cover, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine and the second sensor component is configured to interact with the first sensor component. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

FLOW MEASUREMENT FOR A GAS TURBINE ENGINE

A method of thermodynamic assessment of flow through a turbomachine 10 having a compressor 14, 15, comprising: receiving sensor readings from a plurality of acoustic sensors 42 located about an intake 12 for the turbomachine upstream of the compressor; and receiving pressure and stagnation temperature readings for the flow into the intake. A static temperature is determined for the flow into the intake and an average velocity of the flow over a flow area of the intake upstream of the compressor using the acoustic sensor readings. A mass flow rate of the flow through the intake is determined using the average velocity of the flow and the stagnation pressure.

Sensor system for a pump impeller assembly

Sensor system for a pump impeller assembly

A sensor system 30 measures the position of a metallic impeller 11 in the casing of a pump, eg a slurry pump. An impeller sensor 40 comprises an impeller sensor probe 41 comprising at least one coil 43 mounted to the casing outside one of the wear liners (15),16 disposed between the casing and the impeller 11. A radio frequency drive signal generates an RF field in the coil, and a detector circuit detects a characteristic of the signal developed across the coil 43 that varies with impedance and generates a signal representative of the position of the impeller 11. A clearance signal representing the clearance between the impeller 11 and surface of the wear liner 16 is generated and used to control the position of the impeller relative to the wear liner. A liner sensor 60 including a liner sensor probe 61 may be provided to measure the separation between the liner sensor probe 61 and the surface of the wear liner 16 facing the impeller. The impeller sensor 40 may have plural coils (43, fig ...

Air temperature sensor having a bushing

CONDITION BERWACHUNG OF PUMPS AND PUMPING SYSTEM

CONDITION MONITORING OF PUMPS AND PUMP SYSTEM

AIRCRAFT ENGINE STRUT WITH INTEGRATED SENSOR COMPONENT

An engine strut (100) for providing fan hub frame structural support and monitoring an air flow (116) within an aircraft engine (100) includes an airfoil (120) coupled to the aircraft engine (100) and has a first portion (122) and a second portion (124). The first portion (122) is positioned upstream of the second portion (124) with respect to the air flow. A shield (126) is coupled to the engine (100) and positioned between the first portion (122) and the second portion (124). The shield (126) includes a first side (128) spaced from the first portion (122) and defining a first flow path (164) with the first portion (122). The shield further (126) includes a second side (130) spaced from the second portion (124) and defining a second flow path (169) with the second portion (124). At least one sensor (182) is coupled to the aircraft engine (100) and positioned in flow communication with the second flow path (169).

Neural network for steady state performance approach

Method and system for transmitting sensor signals

DEVICE FOR MEASURING AND COMPLIANCE ASSESSMENT OF IMPACT ON A STRUCTURE

L'invention est relative à un dispositif (100) de mesure et de contrôle de conformité d'un impact (220) sur une structure (200). Il comporte : - un cadre support (10) comportant une face inférieure creuse (13) destinée à être positionnée, en regard de l'impact, contre une surface (210) de la structure (200), la face inférieure creuse définissant un plan de pose (14), - un moyen de mesure dimensionnelle optique (20) configuré pour être dirigé en direction de la face inférieure creuse (13), ledit moyen de mesure dimensionnelle optique étant positionné sur le cadre support (10) à une distance telle que le plan de pose (14) coïncide avec un plan de référence dudit moyen de mesure dimensionnelle optique, - un module de gestion (30) comportant une unité de traitement d'au moins une image obtenue par le moyen de mesure dimensionnelle optique (20) et un écran de visualisation (31) destiné à délivrer une information relative à la conformité de l'impact.

가스 터빈, 가스 터빈의 제어 장치, 가스 터빈의 냉각 방법

... 가스 터빈, 가스 터빈의 제어 장치, 가스 터빈의 냉각 방법에 있어서, 압축기(11)로부터 추기한 압축 공기를 터빈(13)의 디스크 캐비티(31)에 공급하는 냉각 공기 공급 경로(41)와, 냉각 공기 공급 경로(41)에 마련되는 쿨러측 밸브(44)와, 디스크 캐비티(31)의 분위기 온도를 계측하는 온도 계측부(48)와, 온도 계측부(48)가 계측한 분위기 온도에 근거하여 쿨러측 밸브(44)의 개방도를 조정하는 제어 장치(49)를 갖고, 제어 장치(49)는, 쿨러측 밸브(44)에 있어서의 제 1 밸브 개방도 설정값(A1)과, 제 1 밸브 개방도 설정값(A1)보다 큰 제 2 밸브 개방도 설정값(A2)을 갖고, 분위기 온도가 미리 설정된 전환 온도보다 낮을 때에 제 1 밸브 개방도 설정값(A1)을 적용하고, 분위기 온도가 전환 온도보다 높을 때에 제 2 밸브 개방도 설정값(A2)을 적용한다.

método e dispositivo para detectar uma falha de sensor de temperatura em um sistema de turbinas, e sistema para monitorar uma pluralidade de sistemas de turbinas

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.

SITU BLADE MOUNTED TIP GAP MEASUREMENT FOR TURBINES

Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a contact or non-contact displacement probe on a turbine blade that generates data indicative of probe distance from the turbine casing that circumferentially surrounds the blade. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. An optical camera inspection system may be coupled to a turbine blade to obtain visual inspection information within the turbine casing. This method and apparatus provide an accurate and cost effective solution for accessing turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

COMBUSTOR PROBE FOR GAS TURBINE

Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.

Aircraft engine control during icing of temperature probe

Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

Measurement system, machining system, measurement method, and computer-readable recording medium

A measurement system is for measuring positions of a plurality of subjects by using an ultrasonic testing sensor. The measurement system includes an ideal arcuate waveform creation unit configured to create, for each of the subjects, an ideal arcuate waveform of a measurement result of the ultrasonic testing sensor based on machining position information on the subject; a measurement arcuate waveform creation unit configured to create a measurement arcuate waveform based on the measurement result; a position estimation unit configured to collate the ideal arcuate waveform and the measurement arcuate waveform with each other to estimate a position of the subject from the measurement arcuate waveform determined to correspond to any ideal arcuate waveform; and an antiphase waveform addition unit configured to add, to the measurement arcuate waveform, a waveform in antiphase to the measurement arcuate waveform with which the position of the subject has been estimated.

Gas Turbine

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

Blade damage evaluation apparatus, blade damage evaluation method, and blade damage evaluation program

A blade damage evaluation apparatus includes: a registration unit for design information of a turbine and maintenance information; an acquisition processor for detection data of sensors; a first discrimination processor for first facility states of the turbine at a plurality of past time points; a classification processor for classes Cnof a plurality of first facility states; a first determination processor for first operating state values of the turbine; another registration unit for first damage rates at past time points; a setting processor of a characteristic function for each of the classes Cn; a second discrimination processor for a second facility state of the turbine at the current time point; a second determination processor for a second operating state value of the turbine at the current time point; and an analyzer for a second damage rate at the current time point.

УСТРОЙСТВО СЛИВА ТЕКУЧИХ СРЕД ДЛЯ АВИАЦИОННОГО ДВИГАТЕЛЯ

ТУРБИННЫЙ ДВИГАТЕЛЬ И СПОСОБ УПРАВЛЕНИЯ

Verfahren und Systeme zur Überwachung der Funktionstüchtigkeit von Laufschaufeln

Es wird ein System zur Überwachung der Funktionstüchtigkeit eines Rotors präsentiert. Das System enthält ein Verarbeitungssubsystem, das eine Messmatrix auf der Basis mehrerer erster Resonanzfrequenz-Delta-Ankunftszeitvektoren, die einer Laufschaufel und einer ersten Sensorvorrichtung entsprechen, und mehrerer zweiter Resonanzfrequenz-Delta-Ankunftszeitvektoren generiert, die der Laufschaufel und einer zweiten Sensorvorrichtung entsprechen, eine Resonanzmatrix auf der Basis der Messmatrix derart generiert, dass Einträge in der Resonanzmatrix im Wesentlichen linear unkorreliert und linear unabhängig sind, und ein Resonanzsignal unter Verwendung eines ersten Teilsatzes der Einträge der Resonanzmatrix generiert, wobei das Resonanzsignal im Wesentlichen gemeinsame Beobachtungen und Komponenten der mehreren ersten Resonanzfrequenz-Delta-Ankunftszeitvektoren und der mehreren zweiten Resonanzfrequenz-Delta-Ankunftszeitvektoren aufweist.

Pressure sensing apparatus

A pressure sensing apparatus for sensing gas pressure at a pressure tapping 32, the apparatus comprising: a pressure sensor 30 providing a pressure measurement signal of the pressure of a gas admitted into the sensor at a gas inlet port; a gas conduit 31 extending from the inlet port and an end of the conduit distal from the inlet being adapted to receive the gas at the pressure tapping; and a condenser 33 on the conduit, the condenser containing condensation surfaces on which humidity in the gas flowing from the tapping to the inlet condenses out, wherein in operation the temperature at the condenser is lower than at the tapping. In a second aspect the apparatus is used in a gas turbine engine. The pressure sensor may be a resonant cylinder pressure sensor. The pressure sensor may have a heater to maintain an operational temperature higher than the condenser. A thermal sensor may measure the temperature of the pressure sensor. The condensation surfaces may be formed by a spiral wound coil ...

Proximity sensor

TURBOFAN NACELLE ASSEMBLY WITH FLOW DISRUPTOR

... ²A turbofan engine is disclosed which includes a nacelle assembly, having an ²interior ²surface for directing airflow, and a flow disruptor positioned on the interior ²surface ²upstream of the fan, the flow disruptor extending towards the axis a height ²greater than ²the anticipated boundary layer height of the airflow. A turbofan engine which ²includes ²an array of circumferentially disposed flow disruptors extending from a fan ²case inner ²surface is also disclosed. A method of mitigating fan flutter in a gas turbine ²engine by ²generating a circumferential asymmetrically in the airflow, upstream of the ²fan, is also ²described.² ...

ELECTRICAL HARNESS

Harnais électrique pour une turbomachine, comprenant une première terminaison connectée à un appareil (3) apte à émettre un signal électrique, et une deuxième terminaison connectée à un appareil (4) de traitement du signal, caractérisé en ce qu'il comprend un circuit électronique de filtrage du signal, ledit circuit comprenant au moins un composant électronique associé à un seuil de température de fonctionnement, et un moyen d'interruption électrique à déclenchement thermique monté en série ou en parallèle avec ledit composant électronique, ledit moyen d'interruption électrique étant apte à passer d'un état ouvert dans lequel un courant ne peut pas le traverser, à un état fermé dans lequel un courant peut le traverser, ou réciproquement d'un état fermé à un état ouvert, à partir d'une température inférieure ou égale au seuil de température de fonctionnement dudit composant électronique.

ACTUATION SYSTEM UTILIZING MEMS TECHNOLOGY

An actuator (402) includes a pump (705) including a first cavity (708) and a diaphragm (704) coupled in flow communication with the first cavity. The diaphragm is configured to pressurize a fluid contained in the first cavity. The pump further includes a first valve (706) coupled in flow communication with the first cavity. The first valve is configured to release fluid from the first cavity when the first cavity is pressurized. The actuator also includes a piston assembly (712,713) operatively coupled to the pump.

ELECTRIC PROBE ASSEMBLY, GAS TURBINE ENGINE HAVING SAME AND METHOD OF COOLING SAME

A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body. In operation, the conduit carries a fluid flowing at a temperature lower than the local ambient temperature. The at least portion of the probe body is embedded in the fluid inside the conduit. The fluid thermally insulates the probe body from the local ambient temperature of the immediate environment around the at least one electric probe assembly.

Aircraft engine strut with integrated sensor component

METHOD OF TREATING A ROTATIONAL SPEED SIGNAL OF A MOTOR SHAFT OF AIRCRAFT BY NOISE AFFECTS

TURBOMACHINE AND CONTROL METHOD

AERODYNAMIC VARIABLES MEASURING DEVICE FOR PLACEMENT IN A VEIN FLOW OF A TURBOMACHINE

La présente invention concerne un dispositif de mesure de grandeurs aérodynamiques (1) destiné à être placé transversalement dans une veine d'écoulement (12, 13) d'une turbomachine comportant : - un corps amont (2) ayant un profil de forme générale cylindrique définissant un bord d'attaque (5) - une pluralité de capteurs (4), les lignes d'instrumentation (45) des capteurs étant placées dans le corps (2), les éléments sensibles (41) des capteurs s'étendant au niveau du bord d'attaque (5) ; - un carénage aval (3) monté sur le corps amont (2) et définissant un bord de fuite (6) ; le carénage aval (3) comprenant, dans la direction longitudinale du corps amont (2), plusieurs tronçons (35) fixés indépendamment les uns des autres au corps (2), deux tronçons (35) successifs étant reliés par une jonction (37) souple.

INDICATING PAINTING OF TEMPERATURE AND A METHOD FOR PREPARING A SPECIMEN WITH THIS PAINTING

DEVICE FOR MEASURING AND COMPLIANCE ASSESSMENT OF IMPACT ON A STRUCTURE

L'invention est relative à un dispositif (100) de mesure et de contrôle de conformité d'un impact (220) sur une structure (200). Il comporte : - un cadre support (10) comportant une face inférieure creuse (13) destinée à être positionnée, en regard de l'impact, contre une surface (210) de la structure (200), la face inférieure creuse définissant un plan de pose (14), - un moyen de mesure dimensionnelle optique (20) configuré pour être dirigé en direction de la face inférieure creuse (13), ledit moyen de mesure dimensionnelle optique étant positionné sur le cadre support (10) à une distance telle que le plan de pose (14) coïncide avec un plan de référence dudit moyen de mesure dimensionnelle optique, - un module de gestion (30) comportant une unité de traitement d'au moins une image obtenue par le moyen de mesure dimensionnelle optique (20) et un écran de visualisation (31) destiné à délivrer une information relative à la conformité de l'impact.

GAS DOSAGE CONTROL FOR GAS ENGINE

... 가스 엔진 조립체는 압축기, 연소 시스템, 바이패스 라인 및 제어 시스템을 포함한다. 제어 시스템은 이송 지연값에 따라 가스 공급 매개 변수를 제어하도록 구성되어있다. 이송 지연값은 가스 공급 제어 장치가 조절될 때의 시간과 가스 특성에 대응하는 조절을 갖는 가스가 가스 공급 제어기구로부터 하류의 미리결정된 시간에서 수용되는 시간 사이의 지연에 대응한다.

유도 전력 시스템을 포함하는 무선 텔레메트리 시스템

... 연소 터빈 엔진(combustion turbine engine)(10)에서 사용하기 위한 텔레메트리 시스템(telemetry system)으로서, 상기 연소 터빈 엔진(10)은, 터빈 블레이드(turbine blade)와 같은 회전 컴포넌트(rotating component)와 연결된 센서(428), 및 텔레메트리 송신기 회로(telemetry transmitter circuit)(418)를 포함하고, 상기 텔레메트리 송신기 회로(418)는 상기 터빈 블레이드에 부착되고, 상기 센서(428)로부터 상기 텔레메트리 송신기 회로(418)로 전자 데이터 신호(electronic data signal)들을 라우팅(route)하기 위해 상기 센서(428)와 전기적으로 통신한다. 유도 전력 시스템(induction power system)은, 상기 텔레메트리 송신기 회로(418)에 전력을 공급하기 위해 제공되고, 각각의 세라믹 기판(ceramic substrate)들(404) 상에 형성된 1차 평면형 권선(410)을 각각 포함하는 복수의 1차 유도 코일 어셈블리(induction coil assembly)들(400)을 포함하고, 이들은 고정자(180)의 정적 시일 세그먼트(static seal segment)(323) 상에 단-대-단 장착된다. 상기 유도 전력 시스템은 또한, 세라믹 기판(404) 상에 형성된 2차 평면형 권선(412)을 포함하는 2차 유도 코일 어셈블리(402)를 포함하고, 상기 세라믹 기판(404)은 터빈 블레이드 루트(turbine blade root)(132)의 단부면에 장착된다.

ADVANCED TIP-TIMING MEASUREMENT BLADE MODE IDENTIFICATION

A disclosed airfoil health monitoring system and method obtains a signal comprising a waveform indicative of an airfoil path with a sensor. Features of the waveform are determined and compared waveform characteristics indicative of a vibrational mode. A vibrational mode of the airfoil may then be determined based on the comparison between the predetermined waveform characteristics and the obtained waveform indicative of the airfoil path.

ACOUSTIC BREAKTHROUGH DETECTION

Disclosed techniques include creating a pressure differential within an interior of a dual-wall component relative to pressure at an exterior of the dual-wall component, fabricating a hole in a first wall of the dual-wall component, while fabricating the hole in the first wall of the dual-wall component, acoustically monitoring the hole fabrication, while acoustically monitoring the hole fabrication, detecting breakthrough of the first wall of the dual-wall component based on an acoustic signal due to gas passing through the fabricated hole, and based on the acoustic signal, ceasing the fabrication of the hole.

ELECTROMAGNETIC SENSING OF COMPONENTS IN ELECTROMAGNETIC COMMUNICATION AND METHOD

A system of a machine includes a network of a plurality of sensing/control/identification devices distributed throughout the machine, each of the sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals. The system also includes shielding surrounding at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component. The system further includes an electromagnetic sensing system to read the plurality of electromagnetic signals for detection of at least one condition of the sub-system component of the machine. The system yet further includes a remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals.

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 measurement matrix based upon a plurality of resonant-frequency first delta times of arrival vectors corresponding to a blade and a first sensing device, and a plurality of resonant-frequency second delta times of arrival vectors corresponding to the blade and a second sensing device, generates a resonant matrix based upon the measurement matrix such that entries in the resonant matrix are substantially linearly uncorrelated and linearly independent, and generates a resonance signal using a first subset of the entries of the resonant matrix, wherein the resonance signal substantially comprises common observations and components of the plurality of resonant-frequency first delta times of arrival vectors and the plurality of resonant-frequency second delta times of arrival vectors.

Turbomachine cowling with screen

A jet engine includes an external cowling, a member such as an oil reservoir, and a monitoring system for the member that is able to determine information relating to the member. The external cowling includes a visualization screen that is able to communicate with the monitoring system or directly with the member, so as to display the information specific to the member. When installed in the nacelle of the jet engine, this cowling becomes a smart cowling. The system also includes a method for inspecting a member of an aircraft jet engine and a corresponding computer program.

System and method for monitoring the fuel fed to the fuel supply pumps of a gas turbine engine

A system (10) includes a forwarding skid (14) configured to forward a liquid supply from a liquid storage vessel (12) toward a downstream component (20). The forwarding skid (14) includes a pumping system (15) configured to receive a gravity feed of the liquid supply from the liquid storage vessel (12), and the pumping system (15) is configured to pump the liquid fuel supply toward the downstream component (20). The forwarding skid (15) also includes a monitoring system (13) configured to obtain at least one sensed parameter of the gravity feed of the liquid supply received at the forwarding skid (14) upstream from the pumping system (15). The at least one sensed parameter is indicative of a supply level remaining at the liquid storage vessel (12).

METHODS AND SYSTEMS FOR OPERATING AN AIRCRAFT ENGINE

A health parameter for the aircraft engine (110) is monitored by a health evaluation device (240), the health parameter received from a first instrument (230). The health parameter is compared, by the health evaluation device (240), to a predetermined threshold. When the health parameter reaches the predetermined threshold, the health evaluation device wirelessly transmits a fault signal to a controller (210) associated with the aircraft engine (110) to elicit a health response from the controller (210), the fault signal containing at least two mutually-exclusive fault codes associated with an operating condition of the aircraft engine (110) monitored by a second instrument (220).

GAS TURBINE ENGINE SENSOR SYSTEM WITH STATIC PRESSURE SENSORS

A system is provided for an aircraft. This aircraft system includes a gas turbine engine (24) and a sensor system (28). The gas turbine engine (24) includes an inlet (26) and a compressor section (34). A flowpath (58) projects radially inward into the gas turbine engine (24) from the inlet (26) and extends through the compressor section (34). The sensor system (28) includes a plurality of static pressure sensors (76) at least partially within the flowpath (58). The sensor system (28) is configured to determine a total pressure characteristic within the flowpath (58) using the plurality of static pressure sensors (76).

METHOD FOR THE CONTROL OF THE ANTI-ICING SYSTEM OF THE AIRCRAFT GAS TURBINE ENGINE

The invention relates to aircraft deicing systems. A method of controlling a deicing system on an air intake of an aircraft gas turbine engine consists in recording aircraft icing using a unit (1), transmitting icing data from the aircraft system by means of a unit (2) to an electronic regulator (4) of the gas turbine engine, drawing heating air from a compressor of the gas turbine engine, and sending a control signal by means of the electronic regulator to open a valve. The correctness of data transmission from the aircraft system to the electronic engine regulator is also checked, and the air temperature at the inlet to the engine is measured using a sensor (5) arranged on the air intake of the gas turbine engine. Then the measured air temperature at the inlet to the engine is compared with a predetermined maximum value. In the event that a data transmission failure is simultaneously detected when the current value of the temperature is less than the given value, heating air is directed ...

SYSTEMS AND METHODS FOR IMPROVING OPERATION OF PULSE COMBUSTORS

A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.

System and method for measuring clearance between rotating and stationary components of a turbomachine

ANTI-ROTATION PIN FOR COMPRESSION FITTING

A compression fitting is provided. The compression fitting may include a body, a follower, and a pin, and a cap nut. The follower may be disposed within an axial cavity of the body. The pin may be coupled with the follower. The cap nut may be coupled with the body. An internal edge of the cap nut radially overlaps at least a portion of a forward edge of the pin.

Method of measuring the temperature reached by a part, in particular a turbine engine part

A method of measuring temperature reached by a part, for example a turbine engine part, in operation, the method including: mechanically treating the part; oxidizing the part; and depositing a layer including a temperature indicator for indicating the temperature reached by the part in operation.

SENSOR AND TOOTH ARRANGEMENT FOR SHAFT SPEED DETECTION

A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Detection of temperature sensor failure in turbine systems

A method of detecting a temperature sensor failure in a turbine system, includes obtaining individual measurement values from each temperature sensor in a group of temperature sensors, calculating a characteristic value for each temperature sensor in the group based on the measurement values for the corresponding temperature sensor, selecting a first characteristic value among the calculated characteristic values, determining a first maximum value as the maximum of the characteristic values except for the first characteristic value, and determining that the temperature sensor corresponding to the first characteristic value is defective if the first characteristic value is larger than the first maximum value multiplied by a predetermined factor. A corresponding device, system, computer program and computer program product utilize the method.

HEATING SYSTEMS FOR INTERNALLY HEATING ROTOR IN-SITU IN TURBOMACHINES, AND RELATED ROTOR

Heating systems for a rotor in-situ in a turbomachine are provided. In contrast to conventional systems that merely heat from an external turbine casing, embodiments of the disclosure heat the rotor. In one embodiment, a heating system includes a heating element to heat a portion of an exterior surface of the rotor. In another embodiment, the heating system may include a heating element(s) at least partially positioned within the rotor, and the rotor including the heating system. Each embodiment may include a controller to control operation of the heating element(s).

Shaft shear detection through shaft oscillation

There is described a shaft shear event detection method. The method comprises obtaining a demodulated waveform of a shaft oscillation wave superimposed on a shaft rotational speed signal, comparing the amplitude to an amplitude threshold, detecting oscillation when the amplitude threshold is exceeded for a plurality of samples, and detecting a shaft shear when oscillation continues for a predetermined time limit.

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).

Gehäuseanordnung einer Gasturbine

Die Erfindung betrifft eine Gehäuseanordnung einer Gasturbine, die aufweist: ein länglich ausgebildetes Sensorelement (40), das in Längsrichtung gesehen ein vorderes Ende (42) und ein hinteres Ende (41) aufweist; eine erste Gehäusestruktur (10); eine zweite Gehäusestruktur (20), die beabstandet zu der ersten Gehäusestruktur (10) angeordnet ist und die eine Aufnahme (60) für das vordere Ende (42) des Sensorelements (40) aufweist; und eine Führungsstruktur (30), die eine längliche Führungsöffnung (35) für das Sensorelement (40) aufweist. Das Sensorelement (40) erstreckt sich zwischen der ersten Gehäusestruktur (10) und der zweiten Gehäusestruktur (20) und ist dabei entlang eines Abschnitts in der länglichen Führungsöffnung (35) der Führungsstruktur (30) angeordnet, wobei das Sensorelement (40) durch die längliche Führungsöffnung (35) derart ausrichtet und positioniert ist, dass sich sein vorderes Ende (42) in der Aufnahme (60) der zweiten Gehäusestruktur (20) befindet und nur dort befinden ...

STEAM TURBINE CASING POSITION ADJUSTING APPARATUS

Provided is a steam turbine casing position adjusting apparatus that enables the adoption of a small-resolution and small-sized actuator. A steam turbine casing position adjusting apparatus (40) is provided with: a turbine casing (21, 37); a rotor (23); and an actuator (14, 15) for moving the turbine casing (21, 37) along an axial direction. The actuator (14, 15) is disposed radially outside the outer circumferential surface of the turbine casing (21, 37).

Single-axis inspection scope with anti-rotation extension and method for internal inspection of power generation machinery

Internal components of power generation machinery, such as gas turbine engines, are inspected with a spherical, optical-camera inspection system, mounted within a camera housing on a distal end of a compact diameter, single-axis inspection scope. The inspection scope includes nested, non-rotatable telescoping tubes, which define an extension axis. Circumscribing, telescoping tubes have anti-rotation collars, which are in sliding engagement with extension tracks on a circumferential surface of an opposing, nested tube, for ease of extension and retraction of the camera during visual inspections of power generation machinery. The camera is advanced and/or retracted along a scope extension axis by nested, drive tubes, which incorporate at least one external drive screw on a circumscribed drive tube and corresponding female threads formed in a circumscribing drive tube. The spherical camera has a 360-degree field of view, and captures images without rotation about the scope extension axis.

Sensor and tooth arrangement for shaft speed detection

A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

MULTI-STAGE SERIAL TURBO-GENERATOR SYSTEM FOR SUPERCRITICAL CO2 POWER CYCLES

ТУРБИННЫЙ ДВИГАТЕЛЬ И СПОСОБ УПРАВЛЕНИЯ

Изобретение относится к области турбинных двигателей. Способ регулирования по меньшей мере одного двигателя, который содержит компрессор, камеру сгорания, первую и вторую турбины ниже по потоку от камеры сгорания, первый вращающийся вал, удерживающийся с возможностью вращения, по меньшей мере, с упомянутым компрессором и упомянутой первой турбиной, второй вращающийся вал, удерживающийся с возможностью вращения со второй турбиной, причем второй вращающийся вал, тем не менее, может свободно вращаться относительно первого вращающегося вала, включает в себя регулятор для управления подачей топлива к камере сгорания. Упомянутый регулятор отсекает подачу топлива к камере сгорания, если частота (N) вращения упомянутого второго вращающегося вала превышает максимальную пороговую величину (N), которая изменяется как функция по меньшей мере одного индикативного физического параметра, связанного с механической мощностью, извлекаемой из газообразного продукта сгорания посредством второй турбины. Изобретение ...

УЗЕЛ ПОГРУЖНОГО НАСОСА И СПОСОБ ЭКСПЛУАТАЦИИ УЗЛА ПОГРУЖНОГО НАСОСА

Изобретение относится к узлу (1) погружного насоса и способу его эксплуатации. Узел содержит погружной насос (2) с корпусом (3) и капсулу (4) датчика с герметично уплотненным кожухом (5), в которой капсула (4) датчика установлена с возможностью отсоединения в положении (6) датчика, расположенном на внешней поверхности (7) корпуса (3) погружного насоса (2). Погружной насос (2) содержит первичную катушку (8) внутри корпуса (3), и капсула (4) датчика содержит вторичную катушку (9) внутри кожуха (5). Первичная катушка (8) и вторичная катушка (9) выполнены с возможностью индуктивного соединения друг с другом для беспроводной передачи данных и/или мощности через корпус (3) и кожух (5), когда капсула (4) датчика установлена в положении датчика (6). Выдерживается большое давление текучей среды, механическое напряжение и/или нагрев. Способен обеспечить улучшенную беспроводную связь между компонентами во время работы узла погружного насоса. 2 н. и 19 з.п. ф-лы, 12 ил.

Method of positioning a control surface to reduce hysteresis

Turbo-machine assembly

Method and system for transmitting sensor signals

TURBOMACHINE AND LEAK TEST FOR HAS CAPACITIVE SENSORS

L'invention concerne le contrôle de jeux, via des capteurs (53) de déplacement capacitifs montés sur une partie fixe de partie de turbomachine à gaz et comportant individuellement des têtes de mesure (55) orientées vers des cibles d'une partie tournante se déplaçant en face d'eux. Sur la partie fixe, on rend mobiles les capteurs par rapport aux cibles, pour caler les têtes de mesure (55) en vis-à-vis des cibles.

harness and duct with acoustic

Method for determining the temperature in a flow channel of a gas turbine and measuring device

A method for determining temperature in a flow channel of a gas turbine positioned on a testing bench includes: arranging at least one rod-shaped element provided with a thermal paint coating inside the flow channel; operating the gas turbine on the testing bench in a defined operating mode, wherein the thermal paint coating of the at least one rod-shaped element changes its color depending on the temperature that the thermal paint coating is exposed to; detecting the color distribution of the thermal paint coating of the at least one rod-shaped element; and determining the temperature that has been present in the flow channel along the at least one rod-shaped element in the defined operating mode based on the detected color distribution. Another embodiment relates to a measuring device having a rod-shaped element provided with a thermal paint coating.

Electric probe assembly, gas turbine engine having same and method of cooling same

A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body. In operation, the conduit carries a fluid flowing at a temperature lower than the local ambient temperature. The at least portion of the probe body is embedded in the fluid inside the conduit. The fluid thermally insulates the probe body from the local ambient temperature of the immediate environment around the at least one electric probe assembly.

Protected wireless network

A system for a machine component includes at least one local transmitter/receiver. At least one device is associated with a component and configured to communicate with the at least one local transmitter/receiver through wireless signals. Shielding surrounds both the local transmitter and the device for containing the wireless signals proximate to the component. A remote processing unit is disposed outside of the shielding in communication with the local transmitter/receiver. A control system and method are also disclosed.

A WIRELESS TELEMETRY SYSTEM INCLUDING AN INDUCTION POWER SYSTEM

SYSTEM FOR VALIDATING VALIDITY OF SENSOR USING CONTROL LIMIT

The present disclosure relates to a system for validating the validity of a sensor. The present disclosure provides a system for validating the validity of a sensor using a control limit, including an operation unit configured to infer a posterior distribution of a parameter in a Bayesian technique using a prior distribution of the parameter of sensor data and historical data of the sensor, a setting unit configured to set a credible interval for the posterior distribution of the parameter and to set a control line of the sensor data, and a control unit configured to validate the validity of the sensor by monitoring whether the actual measurement data of the sensor deviates the control line. According to the present disclosure, it is possible to set the control limit based on the Bayesian inference and validate the validity of the sensor from the actual sensor data reliably ...

A method of measuring the temperature reached by a part, in particular a turbine engine part

Variable vane control system

Tip clearance control method

Detecting damage to a gas turbine engine

Turbomachines with SAW or BAW devices, measuring arrangements and installation methods

An arrangement is disclosed for measuring an environment parameter at a rotor of a rotary machine; according to some embodiments, the parameter to be measured is temperature and the machine to monitor is a turbomachine. The arrangement includes at least: a SAW or BAW device (512) electrically coupled with an antenna (520), a parameter-sensitive impedance device (532), and two identical cables (542, 544) electrically coupling the SAW or BAW device (512) respectively with the impedance device (532) and a short-circuit (550) or an open-circuit or a matching impedance device. The SAW or BAW device (512) is located in a first zone of the rotor, while the parameter-sensitive impedance device (532) is located in a second zone of the rotor remote from the first zone of the rotor. An interrogator can obtain environment parameter values by sending RF signals to the SAW or BAW device (512) through the antenna (520).

A WIRELESS TELEMETRY SYSTEM INCLUDING AN INDUCTION POWER SYSTEM

A telemetry system for use in a combustion turbine engine (10) comprising a sensor (428) in connection with a rotating component such as a turbine blade, and a telemetry transmitter circuit (418) affixed to the turbine blade and in electrical communication with the sensor (428) for routing electronic data signals from the sensor (428) to the telemetry transmitter circuit (418). An induction power system is provided to power the telemetry transmitter circuit (418) and includes a plurality of primary induction coil assemblies (400) each including a primary planar winding (410) formed on a respective ceramic substrates (404), which are mounted end to end on a static seal segment (323) of a stator (180). The induction power system also includes a secondary induction coil assembly (402) comprising a secondary planar winding (412) formed on a ceramic substrate (404), which is mounted to an end face of a turbine blade root (132) ...

Method of positioning a control surface to reduce hysteresis

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

Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine

A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS 1 ) and by verifying that a first amplitude (A 1 ) of the signal filtered in this way does not exceed a first threshold defined by the manufacturer, by performing second filtering of each signal by a high-pass filter over a short second duration (TPS 2 ) in parallel with said first filtering by a high-pass filter, and by verifying that a second amplitude (A 2 ) of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration (TPS 2 ) being less than the first duration (TPS 1 ), and the second amplitude (A 2 ) being less than the first amplitude (A 1 ).

Aerial vehicle with mission duration capability determination

An aerial vehicle can include oil sensors connected to a lubrication system and a computer connected to the oil sensors. The computer can be programmed to determine mission duration for the unmanned aerial vehicle, determine a maximum oil system duration for the unmanned aerial vehicle based upon data from the oil sensors, perform a comparison of the mission duration to the maximum oil system duration, and output a signal based upon the comparison.

Rotating stall detection using optical measurement of blade untwist

Systems and methods are provided for real-time detection of the onset of stall in turbomachinery, such as compressor stall. The methods are capable of detecting and analyzing time of arrival of the chord of the blade at a sensor array to provide an indication of the onset of compressor stall. Systems for detecting the onset of compressor stall include: light sources; a plurality of linearly arranged optical fibers for transmitting light from the light sources and for receiving transmitted light reflected from a blade; a detector for measuring intensity of the reflected light; and a processor for analyzing the intensity of the reflected light to determine blade twist angle and from the blade twist angle identify onset of compressor stall. The invention can prevent the needless loss of life and assets caused by compressor stall that may lead to unexpected catastrophic failure of an engine.

SYSTEMS AND METHODS FOR MONITORING GAS TURBINE SYSTEMS HAVING EXHAUST GAS RECIRCULATION

A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of extraction passages, wherein the plurality of sensors is configured to measure one or more parameters of the portion of the gas flow traversing the plurality of extraction passages. The system also includes a manifold coupled to the plurality of extraction passages, wherein the manifold is configured to receive the portion of the gas flow from the plurality of extraction passages. The system further includes a return passage coupled to the manifold, wherein the return passage is configured to passively provide the portion of the gas flow to an upstream region of the gas flow path. 1. A system , comprising: a combustor section having one or more combustors configured to combust a fuel and produce an exhaust gas;', 'a turbine section comprising one or more turbine stages disposed downstream from the combustor and configured to be driven by the exhaust gas;', 'an exhaust section disposed downstream from the one or more turbine stages, wherein the exhaust section comprises an exhaust passage configured to receive the exhaust gas from the turbine section; and', 'a gas flow extraction system coupled to the exhaust section and comprising a plurality of extraction passages disposed about the exhaust section, wherein each extraction path is configured to receive a portion of the exhaust gas from a downstream portion of the exhaust passage, wherein the gas flow extraction system is configured to passively route the portion of the exhaust gas to an upstream portion of the exhaust passage via one or more return passages., 'a gas turbine engine, comprising2. The system of claim 1 , wherein each of the plurality of extraction passages comprises one or more sensors.3. The system of claim 2 , wherein the one or more sensors comprise an oxygen ...

SYSTEM AND METHOD FOR CONDITION-BASED MONITORING OF FILTERS

In one embodiment, a system includes an intake section including a filter and one or more strain gauges. The system also includes a processor configured to receive strain information for the filter from the one or more strain gauges and determine an operating condition of the filter based at least in part on the strain information. 1. A gas turbine system comprising:an intake filter of an intake section of the gas turbine system;one or more strain gauges disposed on the intake filter; and receive strain information for the intake filter from the one or more strain gauges; and', 'determine an operating condition of the intake filter based on the strain information., 'a controller communicatively coupled to the one or more strain gauges, wherein the controller is configured to2. The gas turbine system of claim 1 , wherein the operating condition comprises a sealing condition of the intake filter.3. The gas turbine system of claim 1 , comprising a mounting surface that forms a seal in conjunction with the intake filter claim 1 , and wherein the operating condition comprises a sealing condition indicative of a status of the seal.4. The gas turbine system of claim 3 , wherein the controller is configured to determine the sealing condition as unhealthy in response to determining that the strain information is changing faster than a threshold rate of change.5. The gas turbine system of claim 1 , wherein the controller is configured to determine the operating condition as unhealthy in response to determining that the strain information comprises a strain value that is outside of a threshold from a previous strain value.6. The gas turbine system of claim 1 , wherein the operating condition comprises a cleanliness condition of the intake filter.7. The gas turbine system of claim 6 , wherein the controller is configured to instruct a self-cleaning system of the gas turbine system to clean the intake filter based on the cleanliness condition.8. The gas turbine system of claim 1 ...

METHOD FOR CONTROLLING A GAP MINIMIZATION OF A GAS TURBINE

A method for controlling a gap minimization for an adjustable gap between a rotor and a housing of a gas turbine carried out on the basis of a correlation extracted from simulation data. If the actual value (P) lies below the lower threshold (P), the gap minimization is deactivated, whereas if the actual value lies above the upper threshold (P), the gap minimization is activated. The gap minimization is activated between the thresholds (P, P) if the actual value lies above the threshold (P) but is deactivated if the actual value (P) lies below the threshold (P). 1. A method for controlling a gap minimization of an adjustable gap between a rotor and a housing of a gas turbine , wherein the gas turbine comprises a gap-adjusting device , in particular a hydraulic gap-adjusting device , the method comprising:with the aid of a simulation program, the operation of the gas turbine with different parameter settings is modeled and a simulation data set is prepared which contains the dependence of the gap size on an operating parameter,{'sub': U', 'O, 'on the basis of the simulation data set, a lower threshold (P) and an upper threshold (P) for the operating parameter are specified,'}{'sub': U', 'O', 'MAX, 'furthermore, for a transition region (M) between the lower threshold (P) and the upper threshold (P), a correlation (F) between the operating parameter and a maximum value (P) of the operating parameter is extracted from the simulation data set,'}{'sub': I', 'U', 'O, 'during operation of the gas turbine, an actual value (P) of the operating parameter is continuously determined and compared with the lower threshold (P) and the upper threshold (P),'}{'sub': MAX', 'I, 'and the maximum value (P) of the actual value (P) is determined over a specified time period,'}{'sub': I', 'U', 'O', 'I, 'wherein, in the comparison of the actual value (P) with the lower threshold (P) and the upper threshold (P), if the actual value (P){'sub': 'U', 'lies below the lower threshold (P), the gap ...

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

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

METHOD OF COLLECTING RADIATION INFORMATION OF TURBINE BLADE

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

INSTRUMENTATION TRANSFER STRUT

A monolithic lead separator includes a primary lead tube defining a primary channel, a plurality of secondary lead tubes formed monolithically with the primary lead tube, and an instrumentation lead splitter. A cap is positioned in an aperture in the instrumentation lead splitter in a fluid-tight manner. Each of the secondary channels intersects the primary channel. The instrumentation lead splitter is situated at the intersection of the primary channel and the secondary channels. 1. An instrumentation lead separator comprising:a monolithic primary lead tube defining a primary channel;a plurality of secondary lead tubes formed monolithically with the primary lead tube and defining a plurality of secondary channels, each of the secondary channels intersecting the primary channel;an instrumentation lead splitter comprising an aperture situated at the intersection of the primary channel and the secondary channels; anda cap positioned in the aperture in a fluid-tight manner.2. The instrumentation lead separator of claim 1 , and further comprising a plurality of leads claim 1 , each of the leads passing through the primary passage claim 1 , and a portion of the plurality of leads passing through each of the plurality of secondary passages.3. The instrumentation lead separator of claim 2 , wherein the plurality of leads include tubes and wires.4. The instrumentation lead separator of claim 1 , wherein the primary tube channel and the secondary tube channels are substantially smooth to avoid damaging leads passing therethrough.5. The instrumentation lead separator of claim 4 , wherein the intersection between the primary tube channel and the secondary tube channels is also substantially smooth to avoid damaging leads passing therethrough.6. The instrumentation lead separator of claim 1 , and further comprising an airfoil portion surrounding and joined to the primary lead tube.7. The instrumentation lead separator of claim 6 , and further comprising at least one oil tube ...

COOLING HOLE INSPECTION SYSTEM

An inspection system includes a thermographic sensor configured to capture thermographic data of a component having holes as a fluid is pulsed toward the holes, and one or more processors configured to temporally process the thermographic data to calculate temporal scores and spatial scores for the corresponding holes. The scores can be used to obtain a reference dataset and a test dataset. A performance score can be assigned to the component based on the difference between the datasets. 1. A method of performance scoring airflow through a turbine engine component having a first surface and a second surface spaced from the first surface , and a plurality of film holes with inlets formed in the second surface fluidly coupled to outlets formed in the first surface , the method comprising:generating a reference dataset for at least a subset of the plurality of film holes, the reference dataset comprising a reference airflow value indicative of the airflow through the film holes for each of the film holes in the subset of the plurality of film holes, where the reference airflow value is a normalized value;determining a test dataset for a turbine engine component comprising test airflow values for at least some of the film holes in the subset of the plurality of film holes;calculating a difference between the test dataset and the reference dataset; andcalculating a performance score for the turbine engine component based on the difference.2. The method of wherein the normalized value is determined from an aggregate of measured airflow values for multiple turbine engine components.3. The method of wherein the subset of the plurality of film holes comprises all of the plurality of film holes.4. The method of wherein the first surface is an exterior bounding an interior defined by the second surface claim 1 , wherein the interior comprises multiple cooling air circuits and the plurality of film holes comprises different groups of film holes claim 1 , with each grouping ...

Optical based system and method for monitoring turbine engine blade deflection

An optical based system and method for monitoring turbine engine blade deflection during engine operation. An optical camera is coupled the exterior of an engine inspection port, so that its field of view captures images of a rotating turbine blade, such as the blade tip. The camera's image capture or sampling rate matches blade rotation speed at the same rotational position, so that successive temporal images of one or more blades show relative movement of the blade tip within the image field of view. The captured successive images are directed to a blade deflection monitoring system (BDMS) controller. The controller correlates change in a blade's captured image position within the camera field of view between successive temporal images with blade deflection. The BDMS alarms or trips engine operation if the monitored blade deflection falls outside permissible operation parameters.

SHAFT VIBRATION MONITORING SYSTEM AND ROTARY MACHINE

A shaft vibration monitoring system is equipped with a plurality of sensors, a sensor abnormality determination unit, and a shaft vibration monitoring unit. The plurality of sensors detect vibration of the rotary shaft. The sensor abnormality determination unit is configured to compare the detection signals to be output from the plurality of sensors and determine whether an abnormality occurs in at least one of the plurality of sensors. The shaft vibration monitoring unit is configured to monitor the vibration of the rotary shaft, on the basis of the detection signals to be output from the plurality of sensors and the determination result of the sensor abnormality determination unit. 1. A shaft vibration monitoring system of a rotary machine equipped with a rotary shaft and a bearing rotatably supporting the rotary shaft around an axis of the rotary shaft , the shaft vibration monitoring system comprising:a plurality of sensors which are configured to detect vibration of the rotary shaft;a sensor abnormality determination unit which is configured to compare detection signals output from the plurality of sensors and determine whether an abnormality occurs in at least one of the plurality of sensors; anda shaft vibration monitoring unit which is configured to monitor vibration of the rotary shaft on the basis of detection signals output from the plurality of sensors and a determination result of the sensor abnormality determination unit.2. The shaft vibration monitoring system according to claim 1 , wherein a shaft vibration abnormality determination unit which is configured to determine whether an abnormal vibration occurs in the rotary shaft on the basis of detection signals output from the plurality of sensors; and', 'a signal correction unit which is configured to correct a detection signal of the sensor determined to abnormal when the sensor abnormality determination unit determines that an abnormality occurs in at least one of the plurality of sensors., 'the ...

FEEDFORWARD CONTROL OF A FUEL SUPPLY CIRCUIT OF A TURBOMACHINE

A fuel supply system for a turbomachine, comprising a fuel circuit comprising pressurizer at the output of the circuit, a pump arranged to send into the circuit a fuel flow rate which is an increasing function of the rotational speed of a shaft of the pump, and a control circuit arranged to control the device to comply with a flow rate setpoint at the output of the fuel circuit. The system further comprises a feedforward corrector circuit configured to calculate an increment of the flow rate setpoint as a function of the engine speed of the turbomachine and of a variation in the engine speed of the turbomachine, and to add this increment to the flow rate setpoint. A method of regulating the pump is also described.

Calibration for laser inspection

A method of calibrating a laser measurement device includes positioning a calibration part, having known geometric specifications, at varying distances from the laser measurement device (within a measurement depth-of-field of the laser measurement device). The detected geometric specifications, measured at these different positions, are compared with the known specification(s) of the calibration part in order to improve the accuracy of the calibration. A calibration standoff fixture having a plurality of adjustable legs may be used in conjunction with the method to facilitate changing the position of the calibration part relative to the laser measurement device.

SENSOR FAULT DETECTION METHOD

A method of determining a faulty sensor of a sensor array of a gas turbine engine (), the sensor array comprising at least first, second and third sensors (A, B, C), the method comprising the steps of: 110. A method of determining a faulty sensor of a sensor array of a gas turbine engine () , the sensor array comprising at least first , second and third sensors (A , B , C) , the method comprising the steps of:{'b': 1', '1', '1', '1', '1', '1', '1', '1', '1, 'sub': A', 'B', 'C', 'A', 'B', 'A', 'C', 'B', 'C, 'a. measuring a first set of sensor outputs (S, S, S) prior to engine startup from each sensor (A, B, C), and calculating a first difference (S-S, S-S, S-S) in the measured value for each sensor pair (A; B, A;C, B;C);'}{'b': 2', '2', '2', '2', '2', '2', '2', '2', '2, 'sub': A', 'B', 'C', 'A', 'B', 'A', 'C', 'B', 'C, 'b. after a period of time, measuring a second set of sensor outputs (S, S, S) prior to engine startup from each sensor (A, B, C), and calculating a second difference (S-S, S-S, S-S) in measured value for each sensor pair (A;B, A;C, B;C);'}{'b': 1', '1', '2', '2', '1', '1', '2', '2', '1', '1', '2', '2, 'sub': A', 'B', 'A', 'B', 'A', 'C', 'A', 'C', 'B', 'C', 'B', 'C, 'c. calculating a further difference ((S-S) -(S-S), (S-S)-(S-S), (S-S)-(S-S)) between the calculated first and second differences for each sensor pair (A;B, A;C, B;C); and'}d. identifying a failed sensor (A, B, C) where two or more sensor pairs (A;B, A;C, B;C) comprising a common sensor (A, B, C) have a further difference above a predetermined threshold.2. A method according to claim 1 , wherein each of the first claim 1 , second and third sensors comprises a strain gauge transducer claim 1 , and may be configured to sense one of temperature and pressure.3. A method according to claim 1 , wherein each of the sensors is a redundant sensor configured to sense the same pressure or temperature when the engine is running.4. A method according to claim 1 , wherein each of the sensors is located ...

Gas turbine engine particulate ingestion and accumulation sensor system and method

A system and method for determining particulate accumulation in a gas turbine engine includes sensing particulate at a first position that is located at a first side of a gas turbine engine component and supplying a first sensor signal representative thereof, and sensing particulate at a second position that is located at a second side of the gas turbine engine component and downstream of the first position, and supplying a second sensor signal representative thereof, where the second position. The first sensor and second sensor signals are processed to determine the type, quantity, and size of particulate at the first and second positions, respectively. Based at least on the quantity and size of the particulate at the first and the second positions, an amount of the particulate accumulated on the gas turbine engine component is determined.

Oil Monitoring

The oil quality in an oil reservoir of a pump is monitored using the disclosed oil-monitoring sensor. The oil-monitoring sensor includes a first capacitive portion for measuring oil level and a second capacitive portion for measuring dielectric constant of the oil. Changes in dielectric constant of the oil are indicative of degradation of the quality of the oil (e.g., due to contaminants, oxidation, etc.) So oil-monitoring sensor is used to indicate various parameters about the oil quality to an operator. Using the disclosed sensors, the quality of the lubricant and/or cooling oil used by the pump may be monitored without needing to be present at the pump, or without needing to access the interior of the pump (or oil reservoir).

UNIVERSAL HIGH REDUNDANCY SENSOR INTERFACE FOR LOW COST SENSING

A sensing system is provided. The sensing system includes a processor, a sensor node, a plurality of sensors, a power source and a controller. The sensor node is operably connected to the processor on an industrial side and to the sensors on a sensor side. The sensors each measure a parameter of the sensing system and transmit the parameter to the processor via the sensor node. The power source delivers power to the processor. The controller is in operable communication with the processor. The sensor node, disposed in close proximity to the sensors, converts a data protocol for each of the sensors to a different industrial protocol and transmits the converted data through a communication port via the industrial data protocol to the processor. The processor then collects the measurements of each parameter of the plurality of sensors, analyses the measurements and transmits the analyzed data to the controller. 130. A sensing system , comprising:{'b': '34', 'a processor ;'}{'b': 32', '34', '36, 'a sensor node operably connected to the processor and to a plurality of sensors ;'}{'b': 36', '30', '34', '32, 'the plurality of sensors each measuring a parameter of the sensing system and configured to transmit the parameter to the processor via the sensor node ; and'}{'b': 32', '34, 'wherein the sensor node converts a data protocol for each of the plurality sensors to a different industrial data protocol and transmits the converted data through a communication port via the industrial data protocol to the processor ,'}{'b': 32', '36, 'wherein the sensor node is disposed in closer proximity to the plurality of sensors than the processor,'}{'b': 34', '70, 'wherein the processor collects the measurements of each parameter of the plurality of sensors, analyzes the measurements to determine analyzed data, and transmits the analyzed data to a controller .'}2303636. The sensing system as claimed in claim 1 , further comprising a plurality of redundant sensors such that the plurality ...

Using scanned vanes to determine effective flow areas

A computing device for determining effective flow areas of a turbine or turbine engine includes optically scanning and digital modeling of turbine components to produce virtual vanes, virtual vane segments, and virtual ring assemblies. The computing device determines both individual effective flow areas between vanes and the total effective flow area of a vane ring assembly. Based on the virtual vanes and determined effective flow areas, the computing device may compare one or more turbine components to a reference turbine to determine whether the turbine is out of specification and aid in repair, modification, or reassembly of the turbine or turbine engine.

SYSTEM AND METHOD FOR A GAS TURBINE ENGINE SENSOR

A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold. 1. A system , comprising: a combustor section having a turbine combustor that generates combustion products;', 'a turbine section having one or more turbine stages driven by the combustion products;', 'an exhaust section disposed downstream of the turbine section;', 'an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof; and', 'an oxygen sensor disposed in the oxygen sensor adaptor housing, wherein the oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold., 'a gas turbine engine, comprising2. The system of claim 1 , wherein the oxygen sensor comprises at least one of a wideband oxygen sensor claim 1 , a lambda sensor claim 1 , an air/fuel meter claim 1 , or a universal exhaust gas oxygen (UEGO) sensor claim 1 , or any combination thereof.3. The system of claim 1 , wherein the portion of the oxygen sensor comprises at least one of a hex section claim 1 , a gland packing claim 1 , wiring claim 1 , or a connector shell claim 1 , or any combination thereof.4. The system of claim 1 , wherein the oxygen sensor comprises a heater configured to maintain a tip temperature of a tip portion of the oxygen sensor within a temperature range.5. The system of claim 1 , ...

Arrangement, turbo engine and method for the recognition of a shaft breakage of a shaft

An arrangement for detecting a shaft break, including a shaft and a reference shaft that can be rotated together with the shaft, wherein an opening in the shaft overlaps with an opening in the reference shaft in an operational state of the shaft according to the intended use, and a signal conductor that can be severed extends through the two openings and is operatively connected to an evaluation unit, and the evaluation unit is configured to detect a severing of the signal conductor by applying a signal to the signal conductor to detect a shaft break of the shaft. The invention further relates to a turbomachine and a method.

OPTICAL MEASUREMENT DEVICE, OPTICAL MEASUREMENT METHOD, AND ROTATING MACHINE

There is provided: a pair of slanted fiber groups; a pair of parallel fiber groups; a light source for emitting two slanted light beams from a pair of slanted light-emitting fibers, and emitting two parallel light beams from a pair of parallel light-emitting fibers; a target provided to the outer peripheral surface of a rotor; a pair of light-receiving elements for detecting the intensity of light received by each of a pair of slanted light-receiving fibers; a pair of light-receiving elements for detecting the intensity of light received by each of a pair of parallel light-receiving fibers; and a computation unit for performing a computation that includes an interval affected by thermal elongation on the basis of four waveforms indicating changes in the intensity detected by each of the light-receiving elements. 1. An optical measurement device comprising:a pair of first fiber bundles having a pair of first light-emitting fibers, distal ends of which are arranged at a specified interval and a pair of first light-receiving fibers, distal ends of which are arranged at the specified interval, in a light sensor, the pair of first fiber bundles being arranged to be slanted to respectively form two sides of a triangle in triangulation;a pair of second fiber bundles having a pair of second light-emitting fibers, distal ends of which are arranged at the specified interval, and a pair of second light-receiving fibers, distal ends of which are arranged at the specified interval, in the light sensor, the pair of second fiber bundles being arranged in parallel with each other;a light source that outputs light to the pair of first light-emitting fibers and the pair of second light-emitting fibers to emit two slanted light beams from the pair of first light-emitting fibers and emit two parallel light beams from the pair of second light-emitting fibers, whereina target of the light emitted from the first light-emitting fibers and the second light-emitting fiber is provided on an ...

SYSTEMS AND METHODS FOR FAN BLADE DE-ICING

An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade. 1. An anti-ice arrangement for a gas turbine engine , comprising:an engine static structure;a fan blade housed for rotation within the engine static structure; anda magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.2. The anti-ice arrangement of claim 1 , wherein rotation of the fan blade about an engine central longitudinal axis relative to the magnetic field source induces the eddy currents.3. The anti-ice arrangement of claim 2 , wherein the magnetic field source is disposed at least one of radially outward from a tip of the fan blade claim 2 , radially inward from a root of the fan blade claim 2 , or aft of the fan blade.4. The anti-ice arrangement of claim 3 , further comprising a splitter dividing a core flow path and a bypass flow path claim 3 , wherein the magnetic field source is mounted in the splitter.5. The anti-ice arrangement of claim 1 , wherein the magnetic field source is a permanent magnet having a continuously induced magnetic field.6. The anti-ice arrangement of claim 2 , further comprising a tailored resistance coating disposed on the fan blade claim 2 , wherein the resistance coating is configured to increase heat generated by the eddy currents through the tailored resistance coating.7. The anti-ice arrangement of claim 6 , wherein the tailored resistance coating is disposed on at least one of a leading edge of the fan blade claim 6 , a suction side of the fan blade claim 6 , and a pressure side of the fan blade.8. The anti-ice arrangement of claim 2 , further comprising a tailored ...

TURBOCHARGER, VIBRATION DETECTION ASSEMBLY, AND METHOD OF USING SAME

A turbocharger is used within a vehicle and includes an electronic actuator assembly. The electronic actuator assembly includes an actuator housing coupled to at least one of the turbine housing, the compressor housing, and the bearing housing, and an accelerometer coupled to the actuator housing. The accelerometer is adapted to detect vibration of at least one of the turbine housing, the compressor housing, the bearing housing, and the actuator housing thereby obtaining acceleration data of at least one of the turbine housing, the compressor housing, the bearing housing, and the actuator housing to determine rotational speed of the turbocharger shaft. Another embodiment includes a vibration detection assembly having an accelerometer coupled to a vehicle component and the vehicle component is one or more of a turbocharger, a valve assembly, an electronically driven compressor, and a turbocharger having an integral electric motor. 1. A turbocharger for receiving exhaust gas from an internal combustion engine of a vehicle and for delivering compressed air to the internal combustion engine , said turbocharger comprising:a turbine housing defining a turbine housing interior;a turbine wheel disposed within said turbine housing interior for receiving the exhaust gas from the internal combustion engine;a turbocharger shaft coupled to and rotatable by said turbine wheel;a compressor housing defining a compressor housing interior;a compressor wheel disposed within said compressor housing interior and coupled to said turbocharger shaft, with said compressor wheel being rotatable by said turbocharger shaft for delivering compressed air to the internal combustion engine;a bearing housing coupled to and disposed between said turbine housing and said compressor housing, with said bearing housing defining a bearing housing interior, and with said turbocharger shaft disposed within said bearing housing interior; and an actuator housing coupled to at least one of said turbine ...

Adjustable blade outer air seal system

Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.

TURBINE ASSEMBLY AND METHOD FOR FLOW CONTROL

A turbine assembly of an engine is disclosed. The turbine assembly includes a nozzle ring for receiving exhaust gases from a combustion chamber having a plurality of guide vanes for guiding the exhaust gases, a stator ring disposed downstream to the nozzle ring, and a rotor disposed circumferentially within the stator ring. The stator ring includes a plurality of stator vanes adapted to receive the exhaust gases through the guide vanes of the nozzle ring. The stator ring is axially movable between a first position and a second position along at least one cross-key pin disposed between the stator ring and a turbine casing. Each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring. 1. A turbine assembly of an engine , the turbine assembly comprising:a nozzle ring adapted to receive exhaust gases from a combustion chamber of the engine, the nozzle ring comprising a plurality of guide vanes disposed along a circumference of the nozzle ring for guiding the exhaust gases;a stator ring disposed downstream to the nozzle ring, the stator ring comprising a plurality of stator vanes, disposed circumferentially along an inner surface of the stator ring, adapted to receive the exhaust gases through the plurality of guide vanes of the nozzle ring, the stator ring being axially movable between a first position and a second position along at least one cross-key pin disposed between an outer surface of the stator ring and an inner surface of a turbine casing,wherein each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring;anda rotor, disposed circumferentially within the stator ring, adapted to receive the exhaust gases from the stator ring, wherein ...

Adaptive control of coating thickness

An example method that includes receiving a first geometry of a component in an uncoated state and a second geometry of the component in a coated state; determining a first difference between the second geometry and a first simulated geometry based on the first geometry and a first spray law comprising a plurality of first spray law parameters; iteratively adjusting at least one first spray law parameter to determine a respective subsequent spray law; iteratively determining a respective subsequent difference between the second geometry and a subsequent simulated geometry based on the first geometry and the subsequent respective spray law; selecting a subsequent spray law from the respective subsequent spray laws based on the respective subsequent differences; and controlling a coating process based on the selected subsequent spray law.

Adaptive control of coating thickness

An example method that includes receiving a geometry of a component that includes a plurality of locations on a surface of the component; determining a first target trajectory including a first plurality of target trajectory points and a second target trajectory including a second plurality of target trajectory points, the first and second trajectories offset in a first direction, and the first and second plurality of trajectory points offset in a second direction; determining a respective target coating thickness of the coating based on a target coated component geometry and the geometry; and determining a respective motion vector of a coating device based on the first and second target trajectories to deposit the respective target coating thickness.

ACTIVE INLET TURBINE CONTROL

Disclosed are systems and methods for active inlet turbine control. The systems and methods may include receiving a plurality of signals, determining a temperature gradient across an inlet of a gas turbine engine, and transmitting an activation signal to a modulating valve. Each of the plurality of signals may correspond to a temperature measured by one of a plurality of sensors located proximate the inlet of the gas turbine engine. The temperature gradient across the inlet of the gas turbine engine may be determined based on the plurality of signals. The activation signal may be operative to open or close the modulating valve based on the temperature gradient. 1. A method of controlling a gas turbine engine , the method comprising:receiving, at a controller comprising a processor, a plurality of signals, each of the plurality, of signals corresponding to an inlet composition parameter measured by one of a plurality of sensors located proximate an inlet of the gas turbine engine;determining, by the controller, a gradient of the inlet composition parameter across the inlet of the gas turbine engine based on the plurality of signals; andtransmitting, by the controller, an activation signal to a modulating valve, the activation signal operative to open or close the modulating valve based on the inlet composition parameter gradient.2. The method of claim 1 , wherein transmitting the activation signal to the modulating valve includes transmitting the activation signal to one of a plurality of modulation valves.3. The method of claim 2 , wherein each of the plurality of modulation valves is associated with a corresponding one of the plurality of sensors.4. The method of claim 1 , wherein transmitting the activation signal to the modulating valve includes opening the modulating valve in response to the gradient of the inlet composition parameter exceeding a preset value.5. The method of claim 1 , wherein transmitting the activation signal to the modulating valve include ...

DETECTION OF TEMPERATURE SENSOR FAILURE IN TURBINE SYSTEMS

A method of detecting a temperature sensor failure in a turbine system, includes obtaining individual measurement values from each temperature sensor in a group of temperature sensors, calculating a characteristic value for each temperature sensor in the group based on the measurement values for the corresponding temperature sensor, selecting a first characteristic value among the calculated characteristic values, determining a first maximum value as the maximum of the characteristic values except for the first characteristic value, and determining that the temperature sensor corresponding to the first characteristic value is defective if the first characteristic value is larger than the first maximum value multiplied by a predetermined factor. A corresponding device, system, computer program and computer program product utilize the method. 1. A method of detecting a temperature sensor failure in a turbine system , the method comprising:obtaining individual measurement values from each temperature sensor in a group of temperature sensors,calculating a characteristic value for each temperature sensor in the group based on the measurement values for the corresponding temperature sensor,selecting a first characteristic value among the calculated characteristic values,determining a first maximum value as the maximum of the characteristic values except for the first characteristic value, anddetermining that the temperature sensor corresponding to the first characteristic value is defective if the first characteristic value is larger than the first maximum value multiplied by a predetermined factor.2. The method according to claim 1 , further comprising:selecting a second characteristic value among the calculated characteristic values,determining a second maximum value as the maximum of the characteristic values except for the second characteristic value, anddetermining that the temperature sensor corresponding to the second characteristic value is defective if the second ...

Portable industrial air filtration device that eliminates fan-speed sensor error

The present disclosure describes an air filtration device that operates a fan-speed sensor error elimination process. The air filtration device uses a PID control module to ensure its fan operates at a desired fan speed. The fan-speed sensor error elimination process ensures that the air filtration device's controller does not send a measured fan speed determined using data that represent the time it takes the fan blade to complete a fraction of a revolution to the PID control module. This ensures the PID control module accurately controls electrical current supplied to the fan motor.

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

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

TURBINE SPEED DETECTION AND USE

A speed control system and a power load balance detector for a turbine is provided. The speed control system includes a speed wheel with a plurality of teeth. A timer stores a time stamp when each of the teeth passes by a speed probe. A first speed estimate is determined for overspeed protection, and a second speed estimate is determined for operational speed control. The power load balance detector trips or shuts down the turbine when an unbalance is above a first threshold and the speed of the turbine is above a second threshold. 1. A speed control system for a turbine , comprising:a speed wheel attached to and rotatable with the turbine, the speed wheel comprising a plurality of teeth;a speed probe providing an indication each time one of the plurality of teeth passes the speed probe;a timer providing a time stamp for each of the indications;a memory storing each of the time stamps;a first speed estimate based on a difference between two of the time stamps;a second speed estimate based on a difference between two of the time stamps;the first speed estimate being used in an overspeed protection; andthe second speed estimate being used in an operational speed control;wherein the teeth for the time stamps of the second speed estimate are spaced farther apart around the speed wheel than the teeth for the time stamps of the first speed estimate, the first speed estimate thereby being determined quicker than the second speed estimate and the second speed estimate being more accurate than the first speed estimate.2. The speed control system according to claim 1 , wherein the overspeed protection trips or shuts down the turbine.3. The speed control system according to claim 2 , wherein the overspeed protection closes one or more valves to terminate a supply of a fluid or a gas to power the turbine.4. The speed control system according to claim 1 , wherein the operational speed control modulates one or more valves to adjust a supply of a fluid or a gas to power the ...

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.

GAS TURBINE ENGINE WITH AIRFLOW MEASUREMENT SYSTEM

A turbofan gas turbine engine having a bypass duct, and a bypass airflow measurement system. The bypass airflow measurement system comprises: at least one acoustic transmitter configured to transmit an acoustic waveform across the bypass duct of the gas turbine engine though which a bypass airflow passes to at least one acoustic receiver; where the at least one acoustic transmitter and the at least one acoustic receiver are located on an axial plane that is substantially perpendicular to the bypass flow. A method of measuring bypass airflow properties of a turbofan gas turbine engine is also described. 1. A turbofan gas turbine engine having a bypass duct and a bypass airflow measurement system , the bypass airflow measurement system comprising:at least one acoustic transmitter configured to transmit an acoustic waveform across the bypass duct of the gas turbine engine though which a bypass airflow passes to at least one acoustic receiver;where the at least one acoustic transmitter and the at least one acoustic receiver are located on an axial plane that is substantially perpendicular to the bypass flow.2. The turbofan gas turbine engine of claim 1 , wherein the axial plane upon which the at least one acoustic transmitter and the at least one acoustic receiver are located extends from 80° to 100° to the bypass flow.3. The turbofan gas turbine engine of claim 2 , wherein the axial plane upon which the at least one acoustic transmitter and the at least one acoustic receiver are located extends from 85° to 95° to the bypass flow.4. The turbofan gas turbine engine of claim 3 , wherein the axial plane upon which the at least acoustic transmitter and the at least one acoustic receiver are located extends about 90° to the bypass flow.5. The turbofan gas turbine engine of claim 1 , where the at least one acoustic transmitter and the at least one acoustic receiver are mounted in a casing that defines the bypass duct so that they do not substantially protrude into the bypass ...

Flow measurement for a gas turbine engine

A flow machine having a flow passage and an air flow measurement system comprising a plurality of acoustic sensors. The acoustic sensors comprise at least one acoustic transmitter configured to transmit an acoustic waveform through the airflow passing through the flow passage to an acoustic receiver. At least one of the acoustic sensors is rotatable relative to one or more other acoustic sensor.

SYSTEM AND METHOD FOR DISPOSABLE IMAGING SYSTEM

An imaging device includes a plurality of electronic components, a phase change material, and a heat transfer structure. The plurality of electronic components is configured to collect data and have a predetermined temperature parameter. The plurality of electronic components is disposed within the phase change material. The phase change material has a first material phase and a second material phase. The phase change material has a first material phase and a second material phase. The phase change material is configured to absorb heat through changing from the first material phase to the second material phase. The heat transfer structure is disposed within the phase change material. The heat transfer structure is configured to conduct heat within the phase change material. The phase change material and the heat transfer structure are further configured to regulate a temperature of the electronic components below the predetermined temperature parameter. 1. An imaging device comprising:a plurality of electronic components configured to collect data, said plurality of electronic components having a predetermined temperature parameter;a phase change material, said plurality of electronic components disposed within said phase change material, said phase change material having a first material phase and a second material phase, said phase change material configured to absorb heat through changing from the first material phase to the second material phase; anda heat transfer structure disposed within said phase change material, said heat transfer structure configured to conduct heat within said phase change material, wherein said phase change material and said heat transfer structure are further configured to regulate a temperature of said electronic components below the predetermined temperature parameter.2. The imaging device in accordance with claim 1 , further comprising an insulation material claim 1 , said plurality of electronic components disposed within said ...

Creep damage indicator module for a valve and actuator monitoring system

The present application provides a method of evaluating valve creep damage in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors including steam temperatures and steam pressures about the valve over time, generating a design material model for the valve, determining an indicator for consumed creep lifetime based on the steam temperature and steam pressures about the valve over time as compared to the design material model, and altering one or more of the operating parameters and/or initiating repair procedures based upon the consumed creep lifetime indicator.

CONTROL SYSTEM FOR MANAGING STEAM TURBINE ROTOR STRESS AND METHOD OF USE

A control system for a power plant includes a sensor that measures a rotor surface temperature of a steam turbine rotor, where the temperature is a function of exhaust gasses from a heat source for heating steam to a target temperature. The control system includes a controller coupled to the sensor and configured to compute the target temperature using an inverse process model for steam turbine rotor stress dynamics, and based on a reference steam turbine rotor stress and a feedback steam turbine rotor stress, compute a measured steam turbine rotor stress based on a measured surface temperature of the steam turbine rotor, compute an estimated steam turbine rotor stress using a process model for the steam turbine rotor stress dynamics, and based on the target temperature, and compute the feedback steam turbine rotor stress based on the measured steam turbine rotor stress and the estimated steam turbine rotor stress. 1. A control system for a power plant , said control system comprising:a temperature sensor configured to measure a surface temperature of a steam turbine rotor, the surface temperature a function of exhaust gasses from a heat source used to heat steam to a target steam temperature; and compute the target steam temperature using an inverse process model for steam turbine rotor stress dynamics, and based on a reference steam turbine rotor stress and a feedback steam turbine rotor stress;', 'compute a measured steam turbine rotor stress based on a measured surface temperature of the steam turbine rotor;', 'compute an estimated steam turbine rotor stress using a process model for the steam turbine rotor stress dynamics, and based on the target steam temperature; and', 'compute the feedback steam turbine rotor stress based on the measured steam turbine rotor stress and the estimated steam turbine rotor stress., 'a controller coupled to said temperature sensor, said controller configured to2. The control system in accordance with claim 1 , wherein the heat ...

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

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

Method for Operating a Turbo Machine

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

ENGINE CONTROL SYSTEM

An example engine control system may include an oxygen intake sensor; a fuel delivery device to control a rate of fuel delivery to the engine combustor; a combustor pressure sensor; a combustor temperature sensor; and a controller to receive at least one of an oxygen intake signal, a combustor pressure signal, and a combustor temperature signal; determine at least one of a reference specific fuel consumption (SFC) of the engine or a reference amount of a respective exhaust gas of a plurality of exhaust gases based on the oxygen signal, the pressure signal, and the temperature signal; compare at least one of the reference SFC or the reference amount of a respective exhaust gas to a respective threshold value; and control the fuel delivery device to control the rate of fuel delivery based on the comparison. 1. A system comprising:an intake sensor configured to transmit an oxygen signal indicative of an amount of oxygen at an intake of an engine;a fuel delivery device configured to control a rate of fuel delivery from a fuel source to a combustor of the engine;a pressure sensor configured to transmit a pressure signal indicative of a pressure in the combustor;a temperature sensor configured to transmit a temperature signal indicative of a temperature in the combustor; and receive the oxygen signal, the pressure signal, and the temperature signal;', 'determine at least one of a reference specific fuel consumption (SFC) of the engine or a reference amount of a respective exhaust gas of a plurality of exhaust gases based on at least the oxygen signal, the pressure signal, and the temperature signal;', 'compare at least one of the reference SFC or the reference amount of a respective exhaust gas of a plurality of exhaust gases to a respective threshold value; and', 'control the fuel delivery device to control the rate of fuel delivery based on the comparison., 'a controller configured to2. The system of claim 1 , wherein controlling the rate of fuel delivery affects at ...

Gas turbine temperature measurement

The disclosure relates to a method for determining a temperature in a pressurized flow path of a gas turbine comprising the steps of sending an acoustic signal from an acoustic signal emitting transducer across a section of the pressurized flow path, detecting the acoustic signal with a receiving transducer, measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer, calculating the speed of sound, and calculating the temperature as a function of the speed of sound, the heat capacity ratio (□) and a specific gas constant (R spec ) of the gas flowing in the pressurized flow path. Besides the method, a gas turbine with a processor and transducers arranged to carry out such a method is disclosed.

Self-locking plug

A compact, highly-reusable, self-locking includes a body component, a flexible beam finger component with a plurality of axially-oriented flexible beam fingers and one or more outwardly extending tabs, an annular detent ring component including a plurality of detents in radial alignment with the plurality of flexible beam fingers, and a biasing component engaging the flange of the flexible beam finger component and the annular detent ring component for providing a biasing force to urge the flexible finger beam component in a direction of a central, longitudinal axis of the self-locking plug. The flexible beam finger component moves relative to the annular detent ring component when the body component is rotated about the central, longitudinal axis, A, of the self-locking plug, thereby causing the plurality of flexible beam fingers to travel across the plurality of detents and cause elastic deformation of the flexible beam fingers.

Disc shaft center adjusting mechanism in gas turbine

In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.

Method and System for Rotor Stabilization

A system and method for controlling rotor dynamics at a rotor assembly is provided. The system includes a magnetic actuator and a controller. The magnetic actuator is positioned in magnetic communication with the rotor assembly and is configured to obtain a measurement vector corresponding to the rotor assembly and a measurement vector indicative of a rotor dynamics parameter. The magnetic actuator is further configured to selectively output an electromagnetic force at the rotor assembly. The controller is configured to store and execute instructions. The instructions include outputting, via the magnetic actuator, a baseline electromagnetic force to the rotor assembly; obtaining the measurement vector at the rotor assembly from the magnetic actuator; determining non-synchronous vibrations corresponding to the rotor assembly based at least on the measurement vector and a rotor speed of the rotor assembly; determining cross coupled stiffness corresponding to the rotor assembly based at least on the measurement vector, the rotor speed, and a predetermined rotor dynamics model of the rotor assembly; determining an adjusted electromagnetic force of the rotor assembly based at least on the cross coupled stiffness and a damping factor corresponding to the electromagnetic force output from the magnetic actuator; and generating an output signal corresponding to the adjusted electromagnetic force to the rotor assembly.

WIND TURBINE, WIND POWER PLANT AND METHOD FOR CONTROLLING A WIND TURBINE AND A WIND POWER PLANT

A wind turbine having a wake control system that is configured so as to control the wind turbine on the basis of wake effects caused at a further wind turbine, wherein the wake control system is configured so as to achieve control based on a turbulence measured value from a turbulence measurement sensor of the further wind turbine. A wind turbine having a turbulence measurement sensor that is configured so as to determine a turbulence measured value, wherein the turbulence measured value is indicative of a turbulence and/or wind shear at the wind turbine, wherein the wind turbine is configured so as to provide the turbulence measured value in order to control the wind turbine and/or a further wind turbine. A wake control system for a wind turbine, but also an improved wind farm and an improved method for controlling a wind turbine and a wind farm. 1. A first wind turbine comprising:a wake control system configured to control the first wind turbine based on wake effects caused by a second wind turbine, wherein the wake control system is configured to achieve control based on a turbulence measured value from a turbulence measurement sensor of the second wind turbine.2. The first wind turbine as claimed in claim 1 , wherein the turbulence measured value is indicative of a turbulence or wind shear prevailing at a rotor of the second wind turbine.3. The first wind turbine as claimed in claim 1 , wherein the second wind turbine is selected based on at least one: an azimuth position or a determined wind direction.4. The first wind turbine as claimed in claim 1 , wherein the wake control system is configured to control at least one of: an azimuth position claim 1 , a pitch angle claim 1 , a generator torque claim 1 , or a generator power.5. The first wind turbine as claimed in claim 1 , wherein the wake control system is configured to achieve control based on a horizontal wind shear of the second wind turbine.6. The first wind turbine as claimed in claim 1 , wherein the ...

SYSTEMS AND METHODS FOR IMPROVING OPERATION OF PULSE COMBUSTORS

A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes. 1. A pulse combustor system , comprising:a first pulse combustor, comprising a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber at a fuel supply rate, wherein the first pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes; and at least one pressure sensor for measuring a pressure inside the fuel combustor, wherein if the pressure is above a predetermined pressure value, the at least one pressure sensor sends a signal to a controller to adjust a fuel supply rate to the pulse combustor to reduce excitation of the one or more additional oscillation modes; and', 'a first fluid velocity sensor for measuring a first fluid velocity at the inlet pipe and a second fluid velocity sensor for measuring a second fluid velocity at the exhaust pipe, wherein if the first fluid velocity and/or the second fluid velocity is above a predetermined fluid velocity value, the first and/or the second fluid velocity sensor sends a signal to a controller to adjust a fuel supply rate to the pulse combustor to reduce excitation of the one or more additional oscillation modes., 'at least one of2. The ...

Mounting pocket for remote equipment monitoring device

A mounting pocket is provided for attaching a monitoring device to a pump bearing frame. The mounting pocket includes a recessed area located on an external side of the pump bearing frame, a flat surface within the recessed area; and at least four threaded mounting holes extending into the flat surface. At least a part of the drive bearing portion has a reduced radial wall thickness adjacent the flat surface. The threaded mounting holes are configured to receive threaded bolts from the monitoring device to secure the flat surface against a rear surface of the monitoring device. The flat surface is configured to transfer at least one of vibration or thermal energy from the pump bearing frame through the flat surface to the monitoring device.

Damping system for a turbomachine slip ring

A damping system for a turbomachine slip ring includes a slip ring assembly. The slip ring assembly includes a rotating component which is coupled at one end to a rotor shaft of the turbomachine and a stator component which circumferentially surrounds a rotatable center core portion of the rotating component. The system further includes a static structure which defines a carrier sleeve where the carrier sleeve circumferentially surrounds a portion of the stator component. The system also includes a damping material which extends radially between an inner surface of the carrier sleeve and an outer surface of the stator component so as to dissipate vibrational energy of the slip ring assembly during rotation of the rotor shaft.

Optical measurement device, optical measurement method, and rotary machine

The present invention includes: a laser that can change the emission wavelength of light; a light-emitting fiber that emits light output from the laser onto a rotor; a concave surface that is provided in a recessed manner in the rotor and reflects the light emitted from the light-emitting fiber; a light-receiving fiber that receives the light reflected by the concave surface; a photodetector that detects the intensity of the light received by the light-receiving fiber; and a control device that controls the laser and performs optical measurement. The intensity is detected by the photodetector while changing the emission wavelength of the laser; the emission wavelength at which the intensity is largest is selected; and optical measurement is performed by detecting the intensity of light reflected by the concave surface by using light having an emission angle determined by the selected emission wavelength.

FAN WITH REMOTE TEMPERATURE SENSOR AND MOUNTING ARRANGEMENT

A fan includes a temperature sensor, such as a passive infrared sensor, for sensing temperature at a location remote from the fan, such as at a floor, ceiling, or wall, or simply external to the fan housing. This may avoid the influence of heat generated from components of the fan, such as the fan motor or controller for controlling the operation of the fan. A mounting arrangement for forming a connection between two parts, such as components of a fan, is also described. 1. An apparatus , comprising:a fan including a temperature sensor for sensing temperature at a location remote from the fan.2. The apparatus of claim 1 , wherein the temperature sensor comprises a passive infrared sensor.3. The apparatus of claim 1 , wherein the fan comprises an overhead fan with a housing claim 1 , and the temperature sensor is at least partially within the housing of the overhead fan.4. The apparatus of claim 1 , wherein the fan includes a cover claim 1 , and the temperature sensor receives energy through the cover.5. The apparatus of claim 1 , wherein the sensor comprises a body at least partially projecting through an opening in the fan.6. The apparatus of claim 1 , further including a controller for controlling the fan based on the temperature at the remote location.7. The apparatus of claim 6 , wherein the controller is adapted to activate the fan claim 6 , deactivate the fan claim 6 , regulate the speed of the fan claim 6 , or reverse the direction of the fan claim 6 , based on the remote temperature.8. The apparatus of claim 1 , further including a temperature sensor for sensing a local temperature at the fan.9. An apparatus for moving air within a space claim 1 , comprising:a fan including a plurality of blades for moving the air within the space; and a temperature sensor for sensing temperature at a location external to the fan.10. The apparatus of claim 9 , wherein the temperature sensor comprises a passive infrared sensor.11. The apparatus of claim 9 , wherein the fan ...

Systems and methods of servicing equipment

A method of servicing aviation equipment including at least partially-autonomously inspecting components of the equipment using an environmental capture device, wherein at least partially-autonomous inspection includes: capturing information associated with the equipment using the environmental capture device; identifying the components of the equipment using one or more computing devices; determining, by the one or more computing devices, whether each identified component is properly positioned relative to the equipment using reference information; and for components not properly positioned relative to the equipment, determining if there is damage to the component or equipment.

SYSTEM FOR DETECTING ANOMALIES IN GAS TURBINES USING AUDIO OUTPUT

In one embodiment, a turbine system includes a number of sensors, each of the number of sensors disposed in a respective location of the turbine system, and a controller including a memory storing one or more processor-executable routines and a processor. The processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed cause the processor to receive one or more signals from the number of sensors during any stage of operation of the turbine system, and convert the one or more signals to audio output. 1. A turbine system comprising:a plurality of sensors, each of the plurality of sensors disposed in a respective location of the turbine system; and a memory storing one or more processor-executable routines; and', receive one or more signals from one or more of the plurality of sensors during any stage of operation of the turbine system;', 'convert the one or more signals to an audio output characterized by one or more sound waves; and', 'emit the one or more sound waves of the converted audio output as an audible sound via one or more audio output devices; wherein the one or more sound waves emitted by one or more audio output devices enables detection of anomalies, events, or problems present in the respective location., 'a processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed, cause the processor to], 'a controller comprising2. (canceled)3. The turbine system of claim 1 , wherein the plurality of sensors comprises one or more combustion dynamic pressure sensors claim 1 , microphones claim 1 , clearance probes claim 1 , optical probes claim 1 , accelerometers claim 1 , strain gages claim 1 , or some combination thereof.4. The turbine system of claim 1 , wherein the plurality of sensors is configured to sense pressure or vibration waves.5. The turbine system of claim 1 , wherein the one or more routines claim 1 ...

SYSTEM AND METHOD FOR COOLING DISCHARGE FLOW

A system includes a probe disposed through one or more walls of a turbomachine. The probe includes a sensing component configured to sense a parameter of the turbomachine. The probe also includes a body coupled to the sensing component, an inlet configured to receive a cooling inflow, a shell that defines a cooling passage, and an outlet. The sensing component is disposed on a warm side of the one or more walls. The inlet and the outlet are disposed on a cool side of the one or more walls. The cooling passage directs the cooling inflow toward the sensing component and toward the outlet. The outlet is configured to receive an outflow from the cooling passage, wherein the outflow includes at least a portion of the cooling inflow. 1. A system comprising: a sensing component configured to sense a parameter of a turbomachine, wherein the sensing component is disposed on a warm side of the one or more walls;', 'a first body coupled to the sensing component;', 'a first inlet configured to receive a first cooling inflow, wherein the first inlet is disposed on a cool side of the one or more walls;', 'a first shell coupled to the first inlet, wherein the first shell defines a first cooling passage that extends through the one or more walls of the turbomachine, wherein the first cooling passage is configured to direct the first cooling inflow from the first inlet toward the sensing component of the probe and toward a first outlet coupled to the first shell; and', 'the first outlet, wherein the first outlet is disposed on the cool side of the one or more walls, and the first outlet is configured to receive a first outflow from the first cooling passage, wherein the first outflow comprises at least a first portion of the first cooling inflow., 'a first probe disposed through one or more walls of a turbomachine, comprising2. The system of claim 1 , wherein the first probe comprises a lambda probe claim 1 , a temperature probe claim 1 , a flow-sensing probe claim 1 , or a ...

METHOD AND ASSEMBLY FOR INSPECTING ENGINE COMPONENT

One exemplary embodiment of this disclosure relates to a method of inspecting a component of a gas turbine engine. The method includes performing a through-hole inspection, and determining a location of the plurality of holes from results of the through-hole inspection. 1. An inspection assembly , comprising:a controller configured identify a set of pixels adjacent an acceptable hole location along an airfoil section of an engine component, wherein the controller is configured to identify a misaligned hole when a centroid of the set of pixels is outside the acceptable hole location.2. The assembly as recited in claim 1 , further comprising:a thermal imaging camera configured to capture the set of pixels;a fixture for supporting the engine component; anda fluid source in communication with a core passageway of the engine component.3. The assembly as recited in claim 2 , wherein the core passageway is in fluid communication with a plurality of cooling holes on an outer surface of the airfoil section.4. The assembly as recited in claim 2 , further comprising a conduit connecting the fluid source to the core passageway.5. The assembly as recited in claim 1 , wherein the controller is configured to identify partially blocked holes by determining a number of pixels within the set of pixels that are inside the acceptable hole location and determining that the number is greater than zero but below a minimum threshold.6. The assembly as recited in claim 1 , wherein the controller is in communication with a model including the acceptable hole locations.7. The assembly as recited in claim 1 , wherein at least some pixels within the set of pixels are inside the acceptable hole location.8. A method claim 1 , comprising:performing a through-hole inspection on a component of a gas turbine engine, wherein the results of the through-hole inspection include a plurality pixels;identifying a set of pixels adjacent an acceptable hole location along an airfoil section of the component; ...

METHOD FOR ADJUSTING A BAROMETRIC CELL

A method for adjusting a barometric cell may include coupling the barometric cell to a control device via an actuating rod. The actuating rod may be movably mounted on a charging device in any desired position. The method may include applying a freely selectable pressure to the barometric cell so as to bring the actuating rod into contact with a stop, adjusting the barometric cell until a sensor registers a predefined value, and fixing the barometric cell on the charging device. 1. A method for adjusting a barometric cell comprising:coupling the barometric cell to a control device via an actuating rod, wherein the actuating rod is movably mounted on a charging device in any desired position;applying a freely selectable pressure to the barometric cell to bring the actuating rod into contact with a stop;adjusting the barometric cell until a sensor registers a predefined value; andfixing the barometric cell on the charging device.2. The method of claim 7 , wherein the sensor registers a travel of the actuating rod and is integrated in the barometric cell.3. The method according to claim 1 , wherein the adjusting of the barometric cell is done via an actuating device including at least one eccentric claim 1 , the at least one eccentric being connected to the barometric cell at one side and to the charging device on the other side.4. The method according to claim 3 , further comprising turning the eccentric to adjust the barometric cell relative to the charging device.5. A charging device comprising:a barometric cell for actuating a control device,an actuating device for adjusting the barometric cell relative to the charging device, and at least one eccentric connected to the barometric cell on one side and to the charging device on the other side.6. The charging device according to claim 5 , wherein the barometric cell connects to the charging device via a holding device.7. The charging device according to claim 5 , wherein the barometric cell is at least one of a ...

Cement

The present disclosure relates to a cementious composition (e.g. for mounting a strain gauge within a gas turbine engine) comprising: part A comprising an acidic solution of a metal salt; part B comprising silica and one or more metal oxides; and part C comprising colloidal silica and/or a silicate solution. Part A may comprise an acidic aluminium phosphate solution. Part B may comprise one or more or all of titanium oxide, chromium oxide, alumina and barium oxide

Human-machine interface with imaging application

A human-machine interface (HMI), HMI system, turbomachinery package, and method of modifying a partition of an HMI are disclosed. The HMI comprises a first partition storing a first operating system exclusively supporting a primary application; and a second partition storing a second operating system exclusively supporting an imaging application. The HMI system comprises the HMI; an external computing device; a serial cable; and, optionally, a network cable. The turbomachinery package comprises a housing; a gas turbine; a plurality of sensors; a plurality of actuators; and an HMI. The imaging application may be an image deploy function, an image back-up function, and/or an image restore function, any of which can be executed without the use of removable media.

TURBOMACHINE TRAIN AND METHOD FOR COUPLING THE TURBOMACHINE TRAIN

A turbomachine train with two shaft parts which each have a fixedly attached grooved wheel, with a first overrunning clutch, with two rotational speed sensors and with a control device. The clutch is designed to couple and decouple the first shaft part to and from the second shaft part. The first rotational speed sensor measures the rotational speed of the first grooved wheel. The second rotational speed sensor measures the rotational speed of the second grooved wheel. The control device determines the differential angle between the first shaft part and the second shaft part and accelerates the turbomachines, with an acceleration value determined on the basis of the measured rotational speeds and on the basis of the differential angle, such that the two shaft parts couple together at a predetermined target coupling angle. 1. A turbomachine train , comprising:a first shaft section which has a first turbomachine and first slotted wheel which is fixedly attached on the first shaft section,a second shaft section which has a second turbomachine and second slotted wheel which is fixedly attached on the second shaft section,a first overrunning clutch which is designed for coupling the first shaft section to the second shaft section when the rotational speed of the first shaft section is equal to the rotational speed of the second shaft section, and for decoupling the first shaft section from the second shaft section when the rotational speed of the first shaft section is lower than the rotational speed of the second shaft section,a first tachometer which is designed for measuring the rotational speed of the first slotted wheel,a second tachometer which is designed for measuring the rotational speed of the second slotted wheel, anda control device which is adapted to determine the differential angle between the first shaft section and the second shaft section and, at a rotational speed of the second shaft section which is lower than a nominal rotational speed of the ...

TURBINE AND COMPRESSOR BLADE DEFORMATION AND AXIAL SHIFT MONITORING BY PATTERN DEPLOYMENT AND TRACKING IN BLADE POCKETS

A method of monitoring a rotor blade is provided. The method includes disposing a probe including an optical sensor within a mounting hole in a turbine casing of a turbine engine. A laser beam is them emitted by a light source radially inward from the probe position onto a rotor blade tip of the rotor blade The rotor blade is positioned such that it periodically passes the laser beam. The rotor blade tip includes a predetermined pattern The reflected light images from the rotor blade tip are received by the optical sensor From the reflected light images, a blade profile is constructed. Based on this constructed blade profile from the reflected light images off the predetermined pattern a position of the rotor blade is determined. A system of monitoring a rotor blade is also provided. 114. A method of monitoring a rotor blade , comprising{'b': 22', '25', '36, 'disposing a probe including an optical sensor within a mounting hole in a turbine casing of a turbine engine;'}{'b': 54', '22', '100', '14, 'claim-text': [{'b': '14', 'wherein the rotor blade periodically passes the laser beam, and'}, {'b': 100', '120, 'wherein the rotor blade tip includes a predetermined pattern ;'}], 'emitting a laser beam by a light source radially inward from the probe position onto a rotor blade tip of the rotor blade ,'}{'b': 25', '100, 'receiving by the optical sensor reflected light images from the rotor blade tip ; and'}constructing a blade profile from the reflected light images,{'b': 14', '120, 'determining the position of the rotor blade based on the blade profile constructed from the reflected light images off the predetermined pattern .'}2120110100. The method as claimed in claim 1 , wherein the predetermined pattern is deployed in a pocket disposed in the rotor blade tip .3120100100100. The method as claimed in claim 1 , wherein the predetermined pattern is created by a process selected from the group consisting of laser cutting small structures into rotor blade tip claim 1 , ...

SOLID ROCKET MOTOR HEALTH MONITORING

A solid rocket motor includes a case, a solid propellant, and a seal attached to the motor. The seal isolates the solid propellant from a fluid external of the case, and the seal is at least partially transparent. 1. A solid rocket motor , comprising:a case;a solid propellant; anda seal attached to the motor, the seal isolating the solid propellant from a fluid external of the case, wherein the seal is at least partially transparent.2. The solid rocket motor as recited in claim 1 , further comprising a sensor located proximate the seal.3. The solid rocket motor as recited in claim 2 , wherein the sensor is an optical sensor.4. A solid rocket motor claim 2 , comprising:a case;a solid propellant;a seal attached to the motor, the seal isolating the solid propellant from a fluid external of the case;a computing device attached to the seal and connected with a sensor, the computing device including a processor, a memory, and a communication device; andan indicator connected to the computing device, the indicator operable to indicate a health status of the solid rocket motor.5. The solid rocket motor of claim 4 , wherein the processor includes the memory.6. The solid rocket motor of claim 4 , wherein the sensor is in fluid communication with the solid propellant.7. The solid rocket motor of claim 4 , wherein the sensor is in contact with the solid propellant.8. The solid rocket motor as recited in claim 4 , wherein the sensor is configured to generate data indicative of stored health of the solid rocket motor.9. A method for monitoring health of an energetic claim 4 , the method comprising:affixing a smart seal to an energetic device, the smart seal including a sensor;generating a signal from the sensor;recording data representative of the signal from the sensor in a memory;communicating the data from the smart seal to an external computing device;displaying an indication of a health status of the energetic device, wherein the indication is based on the data ...

Enhancing engine performance to improve fuel consumption based on atmospheric rain conditions

Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

STEAM TURBINE BLADE VIBRATION MONITOR BACKPRESSURE LIMITING SYSTEM AND METHOD

A blade vibration monitor backpressure limiting system (BVMBLS), that in addition to direct blade vibration and condenser backpressure monitoring utilizes other plural types of other parallel, real time monitored power plant operation state (OS) information that influences blade vibration. The system references previously stored information in an information storage device that associates respective types of monitored OS information with blade vibration. The BVMBLS determines in real time a likelihood of whether any of the monitored operation states, alone or in combination with other types of monitored operation states, is indicative of a turbine blade vibration safe operation (SO). The BVMBLS determination is utilized to increase or reduce power generation load incrementally so that power efficiency and maximum load is enhanced while turbine blade vibration is maintained in a safe operation state. The previously stored information is updated to new association information. 1. A method for monitoring and controlling power plant steam turbine blade vibration within a designated safe operation range , limiting backpressure on the blades by altering the turbine output load , comprising:sampling in real time with sensors coupled to steam power plant equipment a plurality of types of operation states that impact steam turbine blade vibration, including among others steam turbine blade vibration amplitude and backpressure on the blades;storing in a first automated data storage device at least one sampled data reading for each respective type of operation state; referencing in a second automated data storage device previously stored information associating operation states with steam turbine blade vibration; comparing at least one stored operation state sample reading from each respective type of sampled operation state with respective stored association information relevant thereto and making respective turbine blade vibration safe operation first confidence level ...

ROTATING MACHINE COMPONENT CLEARANCE SENSING SYSTEMS AND METHODS

Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit. 1. A system for measuring a clearance between a rotating machine component and a sensor unit , the system comprising:a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit comprising at least a first sensing element and a second sensing element spaced apart from the first sensing element; and receiving a first waveform from the first sensing element;', 'receiving a second waveform from the second sensing element; and', 'determining, based on a comparison between the first waveform and the second waveform, a distance between the rotating machine component and the sensor unit., 'a sensor processing unit in electrical communication with the sensor unit and configured for2. The system of claim 1 , wherein the first sensing element comprises a first permanent magnet claim 1 , a first pole piece claim 1 , and a first sensing coil claim 1 , and wherein the second sensing element comprises a second permanent magnet claim 1 , a second pole piece claim 1 , and a second sensing coil.3. The system of claim 1 , wherein the sensor unit comprises a magnet and a split pole piece claim 1 , ...

GAS TURBINE HAVING FUEL GAS MONITORING SYSTEM

A gas turbine and a method for operating a gas turbine having a fuel gas monitoring system are presented. The fuel gas monitoring system may provide a measurement of a parameter of a fuel gas in real time. An operation of a gas turbine may be optimized to adapt variation in hydrocarbon content of a fuel gas from the measurement. The fuel gas monitoring system may provide an optical, flow through, online monitoring of fuel gas composition. 1. A gas turbine comprising:a compressor that is configured to compress air;a combustor located downstream of the compressor that is configured to receive the compressed air;a fuel gas supply line connected to the combustor that is configured to supply fuel gas to the combustor, wherein the fuel gas and the compressed air are mixed and combusted in the combustor to generate working gas;a turbine located downstream of the combustor that is configured to expend the working gas to generate power output;a fuel gas monitoring system that is configured to provide a measurement of a parameter of the fuel gas in real time, wherein the fuel gas monitoring system comprises an inlet and an outlet, wherein a fuel gas sample flows into the fuel gas monitoring system through the inlet, wherein the fuel gas sample is discharged from the fuel gas monitoring system through the outlet; anda control system that is configured to adjust an operating parameter of the gas turbine based on the measurement of the parameter of the fuel gas.2. The gas turbine as claimed in claim 1 , wherein the fuel gas monitoring system comprises an optical system.3. The gas turbine as claimed in claim 1 , wherein the fuel gas monitoring system is configured to provide an online measurement of the parameter of the fuel gas.4. The gas turbine as claimed in claim 1 , wherein the fuel gas sample is discharged from the fuel gas monitoring system into the fuel gas supply line.5. The gas turbine as claimed in claim 1 , further comprising an upstream pressure regulating device ...

IGNITION SYSTEM OF AN AIRCRAFT TURBINE ENGINE

A turbine engine ignition system comprising a spark plug having excitation and return terminals, and a spark plug exciter connected to the excitation terminal. The return terminal is connected to an equipotential reference-forming structure, the exciter device is connected to a command line for a signal to supply an excitation signal to the spark plug. The ignition system comprises a control device comprising current and voltage sensors, a first voltage comparator, a second current comparator, and a microcontroller receiving output from the two comparators. The first comparator compares the voltage sensor signal to a first reference value and the second comparator compares the current sensor signal to a second reference value. The microcontroller generates a signal indicating a malfunction of the ignition system if the current sensor signal is lower than the second reference value while the voltage sensor signal is higher than the first reference value. 1. An ignition system of a turbine engine , comprising:an ignition spark plug having an excitation terminal and a return terminal, the return terminal being, in use, connected to an equipotential reference-forming structure of the turbine engine,', 'the exciter device being, in use, connected to a command line and to an electrical power source supplying an excitation signal to the spark plug on reception of an excitation signal over the command line,, 'a spark plug exciter device connected to the excitation terminal of the spark plug,'} the first comparator being configured to compare a value of an amplitude of the signal generated by the voltage sensor to a first reference value and', 'the second comparator being configured to compare a value of the signal generated by the current sensor to a second reference value,', 'the microcontroller configured to implement an AND logic gate whose output is a signal indicative of a malfunction of the ignition system if the value of an amplitude of the signal generated by the ...

METHOD FOR ACTIVE FAULT TOLERANT CONTROL OF TURBOFAN ENGINE CONTROL SYSTEM

A method for active fault tolerant control of a turbofan engine control system designs a linear parameter varying gain scheduling robust tracking controller with good dynamic performance. Adaptive estimation of fault amplitude of a sensor and an actuator is realized according to the change of the operating state of the turbofan engine to accurately reconfigure a fault signal. An active fault tolerant control strategy based on a virtual actuator is designed according to a fault estimation result. Without redesigning the controller, through the designed active fault tolerant control strategy, on the premise of ensuring the stability of the control system, a control effect similar to that of the control system without fault is obtained. 1step 1: establishing a turbofan engine LPV model based on turbofan engine test experimental data:. A method for active fault tolerant control of a turbofan engine control system, comprising the following steps:step 2: designing a LPV gain scheduling robust tracking controller for the turbofan engine LPV model with disturbance;{'sub': 'e', 'claim-text': {'br': None, 'i': x', 'e', 's', 'ds=∫', 'y', 's', 'y', 's', 'ds, 'sub': e', '0', '0', 'r, 'sup': i', 'i, '=∫()(()−())\u2003\u2003(2)'}, 'step 2.1: introducing a new state variable x, defined as'}wherein x∈Ris a state variable u∈Ris the control input of a turbofan engine; d∈Ris a disturbance signal: output is y∈R; the value of a scheduling parameter λ is a normalized relative conversion speed of high pressure rotors of the turbofan engine; λ≤λ≤λ; λand λare respectively a minimum value and a maximum value of the scheduling parameter; system matrices are A(λ)∈R, B(λ)∈R, C∈R, E∈R, G∈R; Rrepresents a (⋅)-dimensional real column vector; and Rrepresents a a×b-dimensional real matrix;wherein e(⋅) is a tracking error and yis a desired tracking signal: rewriting formula (1) into a formula (3) of a generalized formstep 2.2: for the formula (3), constructing and solving the following linear matrix ...

ROTATING COMPONENT SENSING SYSTEM

A sensing system and method for an engine rotor are provided. The rotor is rotatable about a longitudinal axis and at least one rotating member is coupled to rotate with the rotor about the axis. The rotating member comprises at least one marker affixed to a core. The core is made of a first material having a first magnetic permeability and the marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. At least one sensor is mounted adjacent the rotating member and configured to produce at least one first signal in response to detecting passage of the marker as the rotating member rotates about the axis. A control unit is communicatively coupled to the sensor and configured to generate, in response to the first signal received from the sensor, a second signal indicative of at least a rotational speed of the rotor. 1. A sensing system for a rotor of an engine , the rotor rotatable about a longitudinal axis , the system comprising:at least one rotating member coupled to rotate with the rotor about the longitudinal axis, the at least one rotating member comprising a core and at least one marker affixed to the core, the core made of a first material having a first magnetic permeability and the at least one marker comprising a second material having a second magnetic permeability greater than the first magnetic permeability;at least one sensor mounted adjacent the at least one rotating member and configured to produce at least one first signal in response to detecting passage of the at least one marker as the at least one rotating member rotates about the axis; anda control unit communicatively coupled to the at least one sensor and configured to generate, in response to the at least one first signal received from the at least one sensor, a second signal indicative of at least a rotational speed of the rotor.2. The sensing system of claim 1 , wherein the at least one rotating member comprises at least one blade ...

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.

RADIO FREQUENCY WAVEGUIDE COMMUNICATION IN HIGH TEMPERATURE ENVIRONMENTS

A system of a machine includes a network of nodes distributed throughout the machine. A means is operable to communicate with the network of nodes through one or more electromagnetic signals. A plurality of waveguides is configured to guide transmission of the one or more electromagnetic signals. A radio frequency antenna is coupled to a first waveguide of the plurality of waveguides. A radio frequency transceiver is coupled between the means and the radio frequency antenna. A membrane is configured to support communication between the first waveguide and at least one node of the plurality of nodes. 1. A system of a machine , the system comprising:a network of nodes distributed throughout the machine;a means operable to communicate with the network of nodes through one or more electromagnetic signals;a plurality of waveguides configured to guide transmission of the one or more electromagnetic signals;a radio frequency antenna coupled to a first waveguide of the plurality of waveguides;a radio frequency transceiver coupled between the means and the radio frequency antenna; anda membrane configured to support communication between the first waveguide and at least one node of the plurality of nodes.2. The system of claim 1 , wherein the first waveguide comprises a hollow metallic waveguide.3. The system of claim 1 , wherein the radio frequency transceiver is configured to output a pulse train to the radio frequency antenna to broadcast within the first waveguide responsive to the means.4. The system of claim 3 , further comprising a dielectric disk in the first waveguide proximate to the membrane claim 3 , wherein the dielectric disk is configured to generate a plurality of acoustic pressure waves to mechanically vibrate the membrane responsive to the pulse train broadcast through the first waveguide claim 3 , and the at least one node comprises an effector node.5. The system of claim 1 , wherein the at least one node comprises an oscillator and a modulator configured ...

SYSTEMS AND METHODS FOR IMPROVING OPERATION OF PULSE COMBUSTORS

A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes. 1. A method of reducing noise and/or vibration in a pulsejet system , comprising:controlling a rate of fuel supply to a first pulse combustor by a controller, wherein the first pulse combustor comprises a first combustion chamber, a first inlet pipe, a first exhaust pipe, and a first fuel injector for injecting fuel into the first combustion chamber, wherein the first pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes; and at least one pressure sensor attached to the first pulse combustor for measuring a pressure inside the fuel combustor, wherein the at least one predetermined condition comprises the measured pressure inside the fuel combustor exceeding a predetermined threshold pressure value; and', 'at least one fluid velocity sensor attached to the first pulse combustor for measuring a fluid velocity at the inlet pipe or at the outlet pipe, wherein the at least one predetermined condition comprises the measured fluid velocity at the inlet pipe or at the outlet pipe exceeding a predetermined threshold fluid velocity value., 'wherein the controller adjusts a fuel supply rate to the first pulse combustor to reduce excitation of the one or more ...

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).

Observation apparatus, observation method, and non-transitory computer readable medium storing a program

[Object] To observe the sign or occurrence of an unstable operation of a turbo-machine. [Solving Means] An observation apparatus 1 includes: a detection unit 10 including one or two or more sensors 11, 12 that are disposed in a turbo-machine 2, are highly time responsive, and observe unsteady fluctuations of the turbo-machine 2; a computation unit 20 that output signals from the one or two or more sensors 11, 12 every moment, stores time series data for a predetermined period, and calculates in real time a parameter for detecting an unstable operation of the turbo-machine; and a determination unit 30 that compares the parameter for detecting the unstable operation with a predetermined threshold and outputs in real time a determination result of a sign or occurrence of the unstable operation.

AIRFOIL STRUCTURE HAVING A SHAPE MEMORY ALLOY ACTUATOR

A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body. 1. A fan blade for a gas turbine engine , comprising:a blade body having a pressure side disposed opposite a suction side, each of the pressure side and the suction side extending radially from a root towards a tip and extending axially from a leading edge towards a trailing edge, the blade body defining a passageway disposed between the pressure side and the suction side; anda shape memory alloy actuator received within the passageway and operatively connected to the blade body.2. The fan blade of claim 1 , wherein the passageway extends radially between the root and the tip of the blade body.3. The fan blade of claim 2 , wherein the shape memory alloy actuator has a first end that is operatively connected to an internal surface of the blade body proximate the tip and a second end that is operatively connected to the internal surface proximate the root.4. The fan blade of claim 3 , wherein the shape memory alloy actuator is arranged to apply a load to the blade body claim 3 , in response to an operational parameter exceeding a threshold.5. The fan blade of claim 4 , wherein the operational parameter is at least one of a vibration imposed on the blade body.6. A fan blade for a gas turbine engine claim 4 , comprising:a cellular structure that extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge, the cellular structure defining a blade body, the cellular structure having a first portion defining a shape memory alloy ...

DEVICE FOR MEASURING AERODYNAMIC MAGNITUDES INTENDED TO BE PLACED IN A FLOW PASSAGE OF A TURBINE ENGINE

The present invention relates to a device for measuring aerodynamic magnitudes () intended to be placed transversally in a flow passage () of a turbine engine comprising: 2. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the downstream fairing is formed of two sections.3. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the sections have claim 1 , in the longitudinal direction of the upstream body claim 1 , a Young's modulus of over 50 GPa.4. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the flexible junction has claim 1 , in the longitudinal direction of the upstream body claim 1 , a Young's modulus of less than 1 GPa.5. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the flexible junction is made of elastomer.6. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the sections are made of metal.7. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the downstream fairing is fixed to the upstream body by shrinking.8. The device for measuring aerodynamic magnitudes claim 1 , according to claim 1 , wherein the downstream fairing is fixed to the upstream body by means of pins.9. A method for determining the position of at least one flexible junction of a device for measuring aerodynamic magnitudes according to claim 1 , and/or of the number and/or of the position of the pins in a device for measuring aerodynamic magnitudes claim 1 , wherein the downstream fairing is fixed to the upstream body by means of pins claim 1 , wherein it comprises steps of:determining the vibratory frequencies in the flow passage;determining the position of at least one flexible junction in the longitudinal direction of the upstream body and/or the number and/or the position of the pins, such that at least one specific frequency of the device for measuring ...

Method and system for improving parameter measurement

Parameter measurement systems including improved sensor calibration are provided herein. The measurement system includes a first sensor with a first output signal including a plurality of output characteristics, at least one output characteristic being deficient for measuring a desired parameter and at least one output characteristic being suitable for measuring the desired parameter. The measurement system also includes a second sensor with a second output signal comprising at least some of the plurality of output characteristics, the at least one deficient characteristic of the first output signal being suitable in the second output signal for measuring the desired parameter. The measurement system further includes a processor programmed to calibrate the first output signal using the second output signal to generate a third output signal including the at least one suitable characteristic of the first output signal and the at least one suitable characteristic of the second output signal.

Housing arrangement for a gas turbine

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

CRYOGENIC VIBRATION SENSOR AND INSULATOR PAD ASSEMBLY, AND CRYOGENIC PUMPS INCLUDING THE SAME

A cryogenic-rated vibration sensor generally includes a cryogenic-rated accelerometer mounted to a top planar surface of an insulation block, wherein the insulation block includes a threaded opening on a bottom planar surface thereof for attachment to an object. Also disclosed are cryogenic pumps including the cryogenic-rated vibration sensor. 1. A cryogenic-rated vibration sensor comprising:a cryogenic-rated accelerometer mounted to a top planar surface of an insulation block and free from direct contact with a pump component, wherein the insulation block is configured to be adhesively coupled to a pump component such that the cryogenic-rated accelerometer is free from direct contact with a pump component or includes a threaded opening on a bottom planar surface thereof to receive studs from the cryogenic accelerometer and/or the pump component.2. The cryogenic-rated vibration sensor of claim 1 , wherein the insulation block is a polytetrafluoroethylene material.3. The cryogenic-rated vibration sensor of claim 1 , wherein the insulation block is a thermoset reinforced plastic comprising a reinforcing substrate and a thermoset resin binder.4. The cryogenic-rated vibration sensor of claim 3 , wherein the reinforcing substrate is selected from the group consisting of woven glass cloth claim 3 , random glass mat claim 3 , glass filaments claim 3 , woven canvas cotton fabric claim 3 , woven linen cotton fabric claim 3 , paper claim 3 , woven aramid fabric claim 3 , random mat aramid claim 3 , woven graphite fabric claim 3 , and random mat graphite and the thermoset resin binder is selected from epoxies claim 3 , melamines claim 3 , phenolics claim 3 , polyesters claim 3 , and silicones.5. The cryogenic-rated vibration sensor of claim 1 , wherein the insulation block is a glass-cloth reinforced epoxy.6. The cryogenic-rated vibration sensor of claim 1 , wherein the cryogenic-rated accelerometer is a quartz shear-piezoelectric transducer.710. The cryogenic-rated vibration ...

STEAM WETNESS MEASUREMENT WITH MICROWAVE TOMOGRAPHY

A system for measuring steam wetness, including: a plurality of microwave sensors for detecting microwave signals passing through a supply of steam flowing through a cavity; a calibration system for calibrating the plurality of microwave sensors; a film measurement system for measuring a characteristic of a film flowing along an inner surface of the cavity; a system for determining a characteristic of the steam flowing through the cavity based on data provided by the plurality of microwave sensors; and a system for determining a wetness of the steam flowing through the cavity based on the characteristic of the steam flowing through the cavity and the characteristic of the film flowing along the inner surface of the cavity. 1. A system for measuring steam wetness , comprising:a plurality of microwave sensors for detecting microwave signals passing through a supply of steam flowing through a cavity;a film measurement system for measuring a characteristic of a film flowing along inner surface of the cavity;a system for determining a characteristic of the steam flowing through the cavity based on data provided by the plurality of microwave sensors; anda system for determining a wetness of the steam flowing through the cavity based on the characteristic of the steam flowing through the cavity and the characteristic of the film flowing along the inner surface of the cavity.2. The system for measuring steam wetness according to claim 1 , further comprising a calibration system for calibrating the plurality of microwave sensors claim 1 , the calibration system obtaining phase shift and attenuation measurements over a range of frequencies using the plurality of microwave sensors.3. The system for measuring steam wetness according to claim 1 , wherein the cavity comprises a pipe.4. The system for measuring steam wetness according to claim 1 , wherein the plurality of microwave sensors are distributed about a circumference of the cavity.5. The system for measuring steam ...

Detection of deficient sensors in a gas turbine system

Methods and systems for determining that a sensor, such as a pressure sensor, that provides feedback on one or more conditions of a gas turbine is deficient are provided. The amplitude of measurements from the sensor may be monitored in different frequency ranges in order to detect certain abnormal conditions of the gas turbine that require attention by the control system in one frequency range, and also, concurrently and/or separately, detect a sensor deficiency in another frequency range prior to actual failure of the sensor, at which time the failure may otherwise be noticeable in the first frequency range. This permits better detection of deficient sensors during operation of the gas turbine.

Systems and methods for monitoring component strain

A system for monitoring a component is provided. The system includes an electrical field scanner for analyzing an electrical field across a reference zone, and a processor in operable communication with the electrical field scanner. The reference zone may include a plurality of fiducials configured on the component to influence the electrical field. The processor may be operable for measuring an electrical field value along a mutually-orthogonal X-axis and Y-axis, assembling a zone profile including a data point set according to the measured electrical field value. Methods of using the system are also provided.

Calibrating an engine core

A method of calibrating an engine core of a gas turbine engine, wherein the engine core includes a turbine, combustion equipment, a compressor, and a core shaft connecting the turbine to the compressor, the core shaft arranged to drive a propulsive fan of the gas turbine engine, the method including: providing a resistance load on the core shaft, the resistance load arranged to replicate the load of a propulsive fan; driving the engine core; measuring a performance parameter or the engine core; measuring a thrust generated by the engine core; and determining power rating data of the engine core, providing a correlation between the performance parameter and the thrust.

High dynamic range video capture using variable lighting

A system and method is generally provided for producing a high dynamic range video. The system includes a probe and a computer communicatively coupled to the probe. The probe includes a camera and a light source. Further, the probe produces a plurality of frames. The computer includes at least one processor and at least one memory device. The memory device contains instructions configured to combine the plurality of frames into composite frames. The instructions are further configured to filter out portions of frames captured below a first threshold of light and portions of frames captured above a second threshold of light. The light source modulates a lighting characteristic, and the camera captures a first video with the modulated light source to produce a plurality of frames defining a plurality of lighting characteristics. Further, the computer combines the plurality of frames into a second video including a plurality of composite frames.

REMOTE COMMUNICATION AND POWERED SENSING/CONTROL/IDENTIFICATION DEVICES USING HIGH TEMPERATURE COMPATIBLE SEMICONDUCTOR MATERIALS

A system includes a network of a plurality of sensing/control/identification devices distributed throughout a machine, each of the sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals. Shielding surrounds at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component. A communication path is integrally formed in a component of the machine to route a portion of the electromagnetic signals through the component and a remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals, wherein at least a portion of the sensing/control/identification devices comprise a wide band gap semiconductor device and wherein at least a portion of the sensing/control/identification devices comprise an on-chip antenna. 1. A system of a machine , the system comprising:a network of a plurality of sensing/control/identification devices distributed throughout the machine, each of the sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals;shielding surrounding at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component;a communication path integrally formed in a component of the machine to route a portion of the electromagnetic signals through the component; anda remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals, wherein at least a portion of the sensing/control/identification devices comprise a wide band gap semiconductor device and wherein at least a portion of the sensing/control/identification ...

Control system and method for a gas turbine engine

It is provided a control system for a gas turbine engine. Therein, at least one piezoelectric, in particular piezoresistive element arranged at a bearing adapted to support a shaft of the gas turbine engine is provided, wherein the piezoelectric element is adapted to provide information indicative for a force acting on the bearing to a processing unit, wherein the processing unit is adapted to determine a thrust force of the gas turbine engine based on the information provided by the piezoelectric element.

SHAFT SHEAR DETECTION THROUGH SHAFT OSCILLATION

There is described a shaft shear event detection method. The method comprises storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event; monitoring a rotational speed of the shaft; detecting from the rotational speed an oscillation wave superimposed on the rotational speed by detecting a first period below a lower threshold and a second period above an upper threshold, and detecting a rate of occurrence of the first period and the second period, the oscillation wave having a wave modulation frequency corresponding to the rate of occurrence and a wave modulation amplitude; comparing the oscillation signature to the oscillation wave; and detecting the shaft shear event when the oscillation wave corresponds to the oscillation signature. 1. A method for detecting a shear of a rotating shaft positioned between a source and a load , the method comprising:storing in memory a shaft oscillation signature determined as a function of known characteristics of the shaft and associated with a shaft shear event;monitoring a rotational speed of the shaft;detecting from the rotational speed an oscillation wave superimposed on the rotational speed by detecting a first period below a lower threshold and a second period above an upper threshold, and detecting a rate of occurrence of the first period and the second period, the oscillation wave having a wave modulation frequency corresponding to the rate of occurrence and a wave modulation amplitude;comparing the shaft oscillation signature to the oscillation wave; anddetecting the shaft shear event when the oscillation wave corresponds to the shaft oscillation signature.2. The method of claim 1 , wherein the oscillation signature comprises a signature modulation frequency and a signature modulation amplitude claim 1 , and wherein comparing the oscillation wave to the shaft oscillation signature comprises comparing the signature modulation ...

Shaft event detection in gas turbine engines

There is described herein methods and systems for detecting a shaft event in a gas turbine engine comprising a power turbine having a first shaft extending in a first direction and a second shaft extending in a second direction opposite from the first direction. A first speed measurement is obtained at a first location along the first shaft and a second speed measurement is obtained at a second location along the second shaft. A speed ratio is determined between the first speed measurement and the second speed measurement, and is compared to a detection threshold. The shaft event is detected when the speed ratio is beyond the detection threshold.

System and Method for Locating a Probe within a Gas Turbine Engine

A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also include determining a current location of the probe tip within the engine based at least in part on the location-related signals and identifying a virtual location of the probe tip within a three-dimensional model of the engine corresponding to the current location of the probe tip within the engine. Moreover, the method may include providing for display the three-dimensional model of the engine, wherein the virtual location of the probe tip is displayed as a visual indicator within the three-dimensional model. 1. (canceled)2. (canceled)3. (canceled)4. (canceled)5. (canceled)6. (canceled)7. (canceled)8. (canceled)9. (canceled)10. (canceled)11. A system for locating probes within a gas turbine engine , the system comprising:a plurality of location transmitters, each location transmitter being positioned at a known location relative to the gas turbine engine; 'wherein the plurality of location transmitters are positioned within a plurality of access ports of the gas turbine engine, the plurality of access ports differing from the access port through which the probe is inserted; and', 'a probe configured to be inserted through an access port of the gas turbine engine, the probe including a probe tip and a location signal receiver, the location signal receiver being configured to receive location-related signals transmitted from the plurality of location transmitters;'} determine a current location of the probe tip within the gas turbine engine based on the location-related signals received by the location signal receiver and the known locations of the plurality of location ...

COMPONENTS WITH EMBEDDED STRAIN SENSORS AND METHODS FOR MONITORING THE SAME

Components can comprise a substrate, an embedded strain sensor comprising at least two reference points disposed on the substrate, and an outer coating disposed over at least a portion of the embedded strain sensor. 1. A component comprising:a substrate;an embedded strain sensor comprising at least two reference points disposed on the substrate; and,an outer coating disposed over at least a portion of the embedded strain sensor.2. The component of claim 1 , wherein the outer coating covers the entire embedded strain sensor.3. The component of claim 1 , wherein a plurality of coatings are disposed over at least a portion of the embedded strain sensor.4. The component of claim 1 , wherein the outer coating comprises a bond coat or a thermal barrier coating.5. The component of claim 1 , wherein the outer coating comprises a non-transparent material.6. The component of claim 1 , wherein the outer coating is also disposed over at least a portion of the substrate.7. The component of claim 1 , wherein the embedded strain sensor comprises a material that is excited by a wavelength in the electromagnetic spectrum.8. The component of claim 1 , wherein the embedded strain sensor comprises tungsten or platinum.9. The component of claim 1 , wherein the substrate comprises a turbine component.10. The component of claim 1 , wherein the substrate comprises a nickel or cobalt based superalloy claim 1 , and wherein the embedded strain sensor comprises a material more dense than the nickel or cobalt based superalloy.11. A component comprising:a substrate;one or more intermediate coatings disposed on at least a portion of the substrate;an embedded strain sensor comprising at least two reference points disposed on the one or more inner coatings; and,an outer coating disposed over at least a portion of the embedded strain sensor.12. The component of claim 11 , wherein the substrate comprises a turbine component.13. The component of claim 12 , wherein the one or more intermediate coatings ...

HYDROGEN FUEL LEAK DETECTION SYSTEM

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

Wind turbine, wind power plant and method for controlling a wind turbine and a wind power plant

A wind turbine having a wake control system that is configured so as to control the wind turbine on the basis of wake effects caused at a further wind turbine, wherein the wake control system is configured so as to achieve control based on a turbulence measured value from a turbulence measurement sensor of the further wind turbine. A wind turbine having a turbulence measurement sensor that is configured so as to determine a turbulence measured value, wherein the turbulence measured value is indicative of a turbulence and/or wind shear at the wind turbine, wherein the wind turbine is configured so as to provide the turbulence measured value in order to control the wind turbine and/or a further wind turbine. A wake control system for a wind turbine, but also an improved wind farm and an improved method for controlling a wind turbine and a wind farm.

SYSTEM AND METHOD FOR WIND BLADE INSPECTION, REPAIR AND UPGRADE

A method including positioning a modular robotic component proximate an area of interest on a surface of a wind turbine. The modular robotic component including a plurality of modules that perform a plurality of tasks. The method further including inspecting the area of interest with the modular robotic component for an indication requiring at least one of repair or upgrade and operating the modular robotic component to perform the plurality of tasks sequentially as the modular robotic component moves along the surface of the wind turbine. A modular robotic component and system including the modular robotic component are disclosed. 1. A method comprising:positioning a modular robotic component proximate an area of interest on a surface of a wind turbine, the modular robotic component comprising a plurality of modules that perform a plurality of tasks;inspecting the area of interest with the modular robotic component for an indication requiring at least one of repair or upgrade; andoperating the modular robotic component to perform the plurality of tasks sequentially as the modular robotic component moves along the surface of the wind turbine.2. The method as claimed in claim 1 , wherein positioning the modular robotic component comprises positioning an access module comprising a drive mechanism to drive the modular robotic component along the surface of the wind turbine.3. The method as claimed in claim 2 , wherein inspecting the area of interest with the modular robotic component comprises inspecting with an inspection module coupled to the access module claim 2 , the inspection module comprising one or more sensors.4. The method as claimed in claim 3 , wherein operating the modular robotic component to perform the plurality of tasks comprises positioning at least one additional module coupled to the inspection module claim 3 , each additional module performing at least one task of the plurality of tasks.5. The method as claimed in claim 1 , wherein positioning the ...

FULLY INTEGRAL EPOXY CAP PROBE

A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane. 1. A fully integral epoxy cap probe , comprising:a body having a cavity disposed radially outward of a fan blade and comprising a first material;a frame disposed within the cavity and comprising a second material;a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material; anda first soft lead in electronic communication with the first sensor element and the ground plane,wherein the second material and the third material are at least one of a resin, epoxy, and/or thermoset material.2. The fully integral epoxy cap probe of claim 1 , wherein the first material comprises at least one of a composite claim 1 , a resin claim 1 , epoxy claim 1 , and/or thermoset material.3. The fully integral epoxy cap probe of claim 2 , wherein the second material comprises at least one of a hydrophobic dielectric resin claim 2 , epoxy claim 2 , and/or thermoset material comprising bisphenol AF diglycidyl ether having fluorinated methyl groups.4. The fully integral epoxy cap probe of claim 3 , wherein the third material comprises at least one of a hydrophobic conductive resin claim 3 , epoxy claim 3 , and/or thermoset material comprising bisphenol AF diglycidyl ether having fluorinated methyl groups.5. The fully integral epoxy cap probe of claim 4 , wherein the body comprises a first passage wherein the first soft lead is disposed within the first passage.6. The fully integral epoxy cap probe of claim 5 , wherein the frame comprises a first channel aligned ...

ACTIVE SYNCHRONIZING RING

An improved system, apparatus and method for controlling vane angles in a gas turbine engine, and more specifically, for correcting vane angle error in a gas turbine engine. An active synchronization ring comprises a plurality of micro-actuators coupled to the synchronization ring to correct distortion in the synchronization ring. The micro-actuators apply a bending moment to the synchronization ring to cancel or compensate for synchronization ring distortion. The micro-actuators may be controlled open loop or closed loop. Strain sensors measure ring distortion and provide signals to the controller for closed loop control. 1. A system for controlling individual vane angles in a gas turbine engine , comprising:a synchronization ring having a plurality of micro-actuators coupled to said synchronization ring, each of said micro-actuators create a bending moment in said synchronization ring, each of said micro-actuators having an input for receiving a control signal; andan actuator pivotally attached to said synchronization ring for rotating said ring about an axis.2. The system as set forth in claim 1 , wherein said micro-actuators have an input for receiving a control signal.3. The system as set forth in claim 1 , further comprising a controller for generating a control signal to said micro-actuators.4. The system as set forth in claim 3 , wherein said controller provides a command signal to at least one of said micro-actuators when a vane angle error is determined.5. The system as set forth in claim 4 , wherein said controller provides a command signal based upon a scheduled response.6. The system as set forth in claim 3 , further comprising at least one sensor for measuring ring distortion.7. The system as set forth in claim 3 , further comprising a sensor for measuring vane angle.8. An active synchronization ring for controlling individual vane angles in a gas turbine engine claim 3 , comprising:a synchronization ring having a plurality of micro-actuators coupled ...

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 control of coating thickness

An example method that includes receiving a geometry of an uncoated component and a measured coating thickness of a coated test; determining a simulated coating thickness based on the geometry and a first spray law including a plurality of first spray law parameters; determining a difference between the simulated coating thicknesses and the measured coating thickness; iteratively adjusting at least one first spray law parameter to determine a respective subsequent spray law and determining a respective subsequent difference between the measured coating thickness and a subsequent simulated coating thickness based on the geometry and the respective subsequent spray law; selecting a subsequent spray law from the plurality of respective subsequent spray laws based on the respective subsequent differences; and controlling a coating process based on the selected subsequent spray law to compensate for the difference.

STARTER ISSUE DETECTION

Systems and methods for detecting an issue with a starter are provided. One example aspect of the present disclosure is directed to a method for detecting an anomaly with an air turbine starter. The method includes receiving, by one or more controllers, data indicative of a frequency associated with an integrated air turbine starter from one or more sensors located on a stationary portion of the air turbine starter to monitor a rotating portion of the air turbine starter. The method includes determining, by the one or more controllers, an anomaly associated with the integrated air turbine starter based at least in part on the data indicative of the frequency. The method includes providing, by the one or more controllers, a notification indicative of the anomaly associated with the integrated air turbine starter. 1. A method for detecting an anomaly with an air turbine starter , the method comprising:receiving, by one or more controllers, data indicative of a frequency associated with an integrated air turbine starter from one or more sensors located on a stationary portion of the air turbine starter to monitor a rotating portion of the air turbine starter;determining, by the one or more controllers, an anomaly associated with the integrated air turbine starter based at least in part on the data indicative of the frequency; andproviding, by the one or more controllers, a notification indicative of the anomaly associated with the integrated air turbine starter.2. The method of claim 1 , wherein the anomaly associated with the integrated air turbine starter indicates an anomaly with the engine.3. The method of claim 1 , wherein the anomaly associated with the integrated air turbine starter indicates an anomaly with the accessory gearbox..4. The method of claim 1 , wherein at least one of the one or more starter sensors is an accelerometer.5. The method of claim 1 , wherein at least one of the one or more starter sensors is a microphone.6. The method of claim 1 , ...

LIQUID FUEL LEAK DETECTION SYSTEM AND RELATED METHOD

A liquid fuel leak detection system for a gas turbine enclosure including a liquid fuel module is disclosed. The system includes a tube probe array positioned adjacent a floor of the gas turbine enclosure under the liquid fuel module, the tube probe array including at least one tube having at least one opening; and a first hazardous gas sensor panel in communication with the tube probe array, the hazardous gas sensor panel detecting a first accumulation level of turbine liquid fuel vapors in the gas turbine enclosure from the liquid fuel module based on input from the tube probe array, and creating an alarm in response to the detected first accumulation level exceeding a first predetermined amount. A pipe array under a fuel delivery system for detecting fuel leaks thereunder may also be provided. 1. A fuel leak detection system for a gas turbine enclosure for a gas turbine system , the gas turbine enclosure including a liquid fuel module therein , the fuel leak detection system comprising: 'a sensor array positioned adjacent a floor of the gas turbine enclosure under the liquid fuel module, the sensor array including at least one hazardous gas sensor for detecting a first accumulation level of turbine liquid fuel vapors in the gas turbine enclosure from the liquid fuel module, and creating an alarm in response to the at least one hazardous gas sensor detecting the first accumulation level exceeding a first predetermined amount;', 'a liquid fuel module leak detection system including a pipe array positioned adjacent the floor of the gas turbine enclosure and under a fuel delivery system for a combustor of the gas turbine system, the pipe array including at least one pipe having at least one opening therein;', 'a ventilation system including a fan and air flow outlet and an air flow inlet, wherein the fan directs an air flow sweep through the air flow inlet along the floor of the gas turbine enclosure; and', 'a first hazardous gas sensor panel in communication with ...