Temperature measuring system

Fibre optic assembly made from at least three optic fibre bundles

A radiation pyrometer for a gas-turbine engine has a fibre-optic cable (1) with three discrete bundles (11, 12 and 13). At one end (2) of the cable, the bundles are arranged in a jig (21) with one bundle (12) being positioned centrally and the other bundles (11 and 13) which are of C-shape and located on opposite sides of the central bundle. A converging lens (30) may focus radiation from the turbine blades (3) onto the end of the cable, the ends of the bundle being oriented such that each bundle receives radiation from a different region (A, B, and C) spaced along the length of the blades. At the other end (4) of the cable, each bundle is connected to a respective detector (14, 15 and 16). ...

Optical system for determining wear between relatively movable components

An optical apparatus and method for determining wear between relatively movable components, such as between rotor blades 30 and a stator casing 46. The stator casing 46 is provided with an abradable material 48 on its inner surface. A plurality of optical members, optical fibres 52, are arranged at different depths within the abradable material 48 such that a first end 52A of each of the optical fibres is at a different distance from the tips 44 of the turbine rotor blades 30. At least one radiation detector 54 is arranged to detect radiation in the optical fibres. An analyzer 56 is arranged to detect a difference in the radiation collected (i.e. black body radiation) in the optical fibres 52. As the abradable material is worn away the ends of the optical fibres are uncovered in turn and a difference in received optical wavelength is detected. The ends of the optical fibres may be arranged on the surface of a cone or ellipse. Alternatively a single optical member may be provided with a ...

RADIATION PYROMETER

Pyrometric determination of radiance and/ or temperature

A method for determining the radiance and/ or temperature of a rotating object such as a turbine blade B comprises determining the reflectivity of the object B under low-temperature conditions where the object is non-emissive, the radiance of the blade under high temperature conditions and measuring the intensity of incident radiation from external sources such as a combustor C. The radiance measurement may be corrected for reflected radiation by a factor depending on the reflectivity and the incident radiation intensity. A minimum-picking process may be used on the resulting data to reduce the effects of flare. The apparatus may comprise a retractable probe P which rotates about an axis A1. The incident radiation and the radiance of the object may be monitored by two separate detectors D2, D1, or alternatively, by a common pyrometer system (figure 2).

Optical elements

A radiation pyrometer for a gas- turbine engine has a sapphire lens (8) that focusses radiation from the turbine blades (6) onto the end (9) of a fibre-optic cable (10). The front, exposed surface (20) of the lens (8) has a vapour deposited layer (21) of platinum aluminium oxide which acts as a catalyst to promote oxidation of soot to a gaseous form and thereby reduce contamination of the lens. ...

Detection of changes in light-affecting-characteristics of optical elements

In a radiation pyrometer in a gas turbine engine, non-uniformly distributed changes in transparency of an optical element in the system, e.g. contamination of pyrometer objective lens L1 by combustion products from the turbine can be automatically detected. Lens L1 focusses radiation from target T onto an additional lens L2, which in turn focusses it onto the end E of the fibre-optic bundle F. Considered reciprocally, lens L2 images the end E of fibre-optic F into L1, so that although each optical fibre in end E receives radiation from all parts of target T, each fibre is imaged into a corresponding discrete area of L1. Fibre-optic bundle F comprises two (or more) sub-bundles F1 and F2 forming complementary sub-areas of end E and each sub-bundle is provided with its own photodetector P1, P2 and associated pre-amplifier A1,A2 adjusted so that their outputs A1S1 and A2,S2 are matched at the non-contamination condition. When one part of lens L1 is contaminated during service more than the ...

RADIATION PROBE

High temperature seal assembly for optical sensor

TIME-DISSOLVED THERMALGRAPHIC MEASUREMENT OF A LAYER OF METAL THICKNESS

Temperature sensor in particular for gas turbines

Thermal picture giving system for a turbine.

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

Thermal picture giving system for a turbine.

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

ELECTRO-OPTICAL APPARATUS INCLUDING A PHOTODETECTOR ARRAY.

Electro-optical apparatus comprising a network of photodetectors

L'invention concerne un appareil électro-optique tel qu'un pyromètre, dans lequel une image d'un rayonnement est formée sur un dispositif détecteur sensible à ce rayonnement. Le dispositif détecteur comporte quatre photodiodes rectangulaires (21 à 23) disposées en un réseau orthogonal (20). Le rayonnement d'un corps chaud est focalisé sous la forme d'une image circulaire (25) centrée sur le réseau. Les sorties des photodiodes opposées en diagonale (21 et 23, 22 et 24) sont connectées deux à deux pour former deux canaux de sortie identiques (28, 29). En cas de déplacement de l'image par rapport à la position centrée, les variations (A1 à A4) des aires concernées des photodiodes se compensent deux à deux dans chaque canal. Application aux pyromètres et à d'autres appareils électro-optiques ayant au moins deux canaux électriques de sortie.

Optical sensor of temperature

L'invention concerne un capteur optique agencé de façon à minimiser les erreurs de mesure résultant du rayonnement thermique émis par des organes internes du capteur. Le capteur comporte une sonde tubulaire (1) dont l'extrémité avant contient un élément en saphir (24) dans une chambre de stagnation (23) où le gaz chaud à mesurer circule et chauffe un revêtement thermiquement émetteur (25) dudit élément (24). Une lentille (36) focalise le rayonnement sur une extrémité d'un câble à fibres optiques (2) logé dans l'arrière de la sonde et refroidi par de l'air comprimé circulant dans la sonde. Cet air s'échappe par un orifice (35) situé en arrière d'une barrière thermique transparente (31) qui protège l'élément en saphir (24) contre le refroidissement. Application à la mesure de température dans une turbine à gaz. The invention relates to an optical sensor arranged to minimize measurement errors resulting from thermal radiation emitted by internal components of the sensor. The sensor comprises a tubular probe (1) whose front end contains a sapphire element (24) in a stagnation chamber (23) where the hot gas to be measured circulates and heats a thermally emitting coating (25) of said element (24). ). A lens (36) focuses the radiation on one end of an optical fiber cable (2) housed in the rear of the probe and cooled by compressed air flowing through the probe. This air escapes through an orifice (35) located behind a transparent thermal barrier (31) which protects the sapphire element (24) against cooling. Application to temperature measurement in a gas turbine.

OPTICAL ELEMENT FOR PYROMETRIC MEASUREMENTS

APPARATUS OF TRANSMISSION Of a RADIATION

SELF VALIDATING GAS TURBINE ENGINE FLAME DETECTION SYSTEM USING DUEL OPTICAL VERIFICATION

A self validating flame detection system (10) for a turbine engine (12) configured to determine whether a flame exists in a turbine engine combustor (16) is disclosed. The self validating flame detection system (10) may include two different types of flame detection sensors (18) to reduce the risk of false positive signals. In at least one embodiment, the flame detection system (10) may include one or more infrared sensors (20) that sense infrared radiation within the combustor (16) of the turbine engine (12) and one or more ultraviolet light sensors (22) that sense ultraviolet light within the combustor (16) of the turbine engine (12). The flame detection system (10) may include a processor (24) configured to ignore the steady state infrared signal generated and instead analyze the dynamic infrared signal. The processor (24) may be configured to determine whether both types of sensors (18) indicate a flame out condition so that a false alarm does not occur.

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

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

Apparatus for measuring temperature of aero-engine turbine blades

An apparatus for measuring temperature of turbine blades, including: a radiation collection device, a data processing module; a master control unit (MCU); a calibration module; and a motion servo. The radiation collection device includes a scan reflector, a collimator lens, a first dichroic mirror, a first focus lens, a visible and near-infrared (VNIR) detector, a second dichroic mirror, a second focus lens, a short-wave infrared (SWIR) detector, a third focus lens, and a medium-wave infrared (MWIR) detector. The calibration module includes a calibration reflection mirror and a blackbody furnace. The scan reflector, the collimator lens, the first dichroic mirror, the second dichroic mirror, the third focus lens, and the MWIR detector are disposed successively along a first optical axis; the first dichroic mirror, the first focus lens, and the VNIR detector are disposed successively along a second optical axis that is perpendicular to the first optical axis.

Temperature sensor for a high speed rotating machine

Infra-red sensors are often used in turbo molecular pumps to detect the temperature of the rotor or other mechanical parts and therefore indicate imminent, or potential, running failures. As deposits build up on either the infra-red sensor, or on the surface being monitored, the reading given by the sensor may not be a true representation of the actual surface temperature which can cause the pump controller to fail to stop the pump in time. The present invention provides a method and device for calibrating the sensor by creating a determined temperature rise in the sensor whilst keeping the rotor at ambient temperature. In particular the present invention uses the motor stator as the heater for causing the temperature increase.

ДИАГНОСТИЧЕСКИЙ СТЕНД ДЛЯ ВЕТРЯНОЙ ТУРБИНЫ

Изобретение относится к устройствам контроля температуры и диагностики комплектующих ветрогенератора (подшипников и обмоток электродвигателей). Заявлен диагностический стенд для ветряной турбины, включающий канал передачи от источника ИК-излучения, связанный с источником ИК-излучения, при этом в качестве источника ИК-излучения используют подшипники или обмотки турбины. Стенд представляет собой станину, выполненную с возможностью фиксации на ней электродвигателя ветряной турбины в корпусе фланцем-зажимом таким образом, чтобы инфракрасный модуль связи, расположенный на опоре, зафиксированной к станине, находился напротив светодиодов, а индикаторы светодиодов - на внешней поверхности корпуса турбины. Причем сами светодиоды подключены к диагностическим датчикам температуры и тока, выполненным с возможностью фиксации на узлах турбины. На станине напротив места расположения турбины установлен асинхронный трехфазный электродвигатель переменного тока, на валу которого установлена эластичная муфта ...

СПОСОБ МОНИТОРИНГА ИНТЕРЕСУЮЩЕЙ ВЫСОКОТЕМПЕРАТУРНОЙ ОБЛАСТИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

... 1. Способ мониторинга интересующей высокотемпературной области газотурбинного двигателя, содержащий этапы, на которых:берут стационарную лопатку с внутренним охлаждением;в этой стационарной лопатке размещают порт для наблюдения; иоперативно соединяют прибор для мониторинга с портом для мониторинга для создания поля обзора интересующей области.2. Способ по п. 1, далее содержащий этап, на котором собирают данные об интересующей области с помощью устройства для сбора данных, соединенного с прибором для мониторинга.3. Способ по п. 2, при котором прибор для мониторинга содержит наблюдательный прибор, а устройство для сбора данных содержит инфракрасный формирователь изображений, и при котором этап сбора данных из интересующей области содержит этап, на котором собирают данные об изображении интересующей области с помощью наблюдательного прибора, соединенного с инфракрасным формирователем изображения.4. Способ по п. 2, при котором этап сбора данных из интересующей области содержит этап, на котором ...

КОРПУС ИЗМЕРИТЕЛЬНОГО УСТРОЙСТВА

... 1. Корпус (10) измерительного устройства для бесконтактно регистрирующего физическую величину компонента датчика или подобного датчика, содержащий:- соединительное устройство (12) для подвода, по меньшей мере, одной охлаждающей и/или промывающей среды (22, 24, 26) и, по меньшей мере, одного провода для передачи сигнала во внутреннюю часть корпуса или в стенку корпуса,- расположенную в соединительном устройстве (12) направляющую трубу (14) с продольной осью (20) и- головку (18) зонда, фиксированную с возможностью разъединения, предпочтительно, завинченную на противоположном соединительному устройству (12) конечном участке (16) направляющей трубы (14), выполненной с возможностью проводить к головке (18) зонда или принимать, по меньшей мере, одну охлаждающую среду (22, 24, 26) и, по меньшей мере, один провод для передачи сигнала, отличающийся тем, чтоголовка (18) зонда и конечный участок (16) имеют соответственно радиально продолжающиеся относительно продольной оси (20) проходы (34) для передачи ...

System und Verfahren zur Steuerung von Brennkammerbetriebsbedingungen auf der Basis einer Flammendetektion

Es wird ein System (10) offengelegt, das einen Brenner (20) mit einem Abschlussdeckel (28) und wenigstens einer sich von einer Innenseite (27) des Abschlussdeckels (28) aus erstreckenden Brennstoffdüsenanardnung (30) enthält. Eine Patrone (46) kann sich durch den Abschlussdeckel (28) hindurch und in die Brennstoffdüsenanordnung (30) erstrecken. Die Patrone (46) kann eine Öffnung (85) zur Aufnahme von aus dem Inneren des Brenners (20) emittiertem Licht definieren. Zusätzlich kann ein faseroptisches Kabel (48) in der Patrone (46) angeordnet sein und kann dafür ausgelegt sein, wenigstens einen Teil des durch die Öffnung (85) aufgenommenen Lichtes zu erfassen.

Method and apparatus for detecting the presence of flame in the exhaust path of a gas turbine engine

ELECTRO-OPTIC APPARATUS

Optical radiation pyrometer

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

PYROMETER APPARATUS

FLAME DETECTION METHOD AND APPARATUS FOR GAS TURBINE EXHAUST PATH

A method and apparatus for monitoring gas turbine exhaust for unwanted flames employs a system comprising an electro-optics module (40), sensors (44), processing electronics (45), and collection and transmitting optics (20, 30). Information generated by the sensor can suggest problems with combustion related components.

RADIATION-RESPONSIVE APPARATUS

Known radiation pyrometers have a lens mounted at the forward end of a tube that is located within an outer tube which is supplied with purge gas. In the present invention, the lens is mounted in a rear portion of an inner tube that is stepped to a forward portion of reduced diameter that is open at its forward end. The outer tube extends coaxially around the inner tube and is separated from it by an annular gas passage. The outer tube has an aperture at its forward end that is smaller than the external diameter of the forward end of the inner tube and larger than its internal diameter. Gas inlets in the outer tube open into the passage, the inlets being located rearwardly of the forward end of the inner tube, and the area of the gas inlets being greater than the gap between the forward end of the inner tube and the outer tube. Gas flows through the inlets, along the passage, across the forward end of the inner tube and out the apertures thereby setting up a substantially constant pressure ...

In the thermal Image detecting passage

REFLECTIVE ELEMENTS AND DETECTORS COMPRISING OF THE REFLECTIVE ELEMENTS

ELEMENTS REFLECHISSANTS ET DETECTEURS COMPORTANT DES ELEMENTS REFLECHISSANTS

UN PYROMETRE A RADIATION 1, OU AUTRE DETECTEUR OPTIQUE, A UN ENSEMBLE MIROIR 20 CAPABLE DE SUPPORTER DE HAUTES TEMPERATURES. L'ENSEMBLE MIROIR EST UN BLOC D'ACIER CONTENANT ENTRE 15 ET 20 DE CHROME, 4,0 ET 5,2 D'ALUMINIUM, 0,05 ET 0,4D'YTTRIUM, 0,2 ET 0,4 DE SILICONE ET ENTRE 0,00 ET 0,003 DE CARBONE. UNE SURFACE REFLECHISSANTE 24 SUR L'ENSEMBLE EST CONSTITUEE PAR UNE COUCHE D'OXYDE D'ALUMINIUM 27. L'ENSEMBLE EST FORME PAR CHAUFFAGE D'UN CORPS EN ACIER DE FACON A PRODUIRE LA COUCHE D'OXYDE D'ALUMINIUM QUI SERA ENSUITE POLIE JUSQU'A UN FINI REFLECHISSANT. APRES CHAUFFAGE, LE CORPS EST USINE A LA FORME DESIREE DE L'ENSEMBLE MIROIR.

SYSTEM OF DETECTION Of CHIPPING IN an ENGINE HAS TURBINE

Dans un mode de réalisation, un système (10) inclut un système de pyrométrie multi-spectral (36) configuré pour recevoir un signal de rayonnement à large bande de longueurs d'onde (80) depuis un composant de turbine (56), pour séparer le signal de rayonnement à large bande de longueurs d'onde (80) en de multiples signaux de rayonnement à bande de longueurs d'onde étroite (94), pour déterminer l'émissivité (122) du composant de turbine (56) en fonction des signaux de rayonnement à bande de longueurs d'onde étroite (94), et pour détecter de l'écaillage (104) sur une surface du composant de turbine (56) en fonction de l'émissivité (122). In one embodiment, a system (10) includes a multi-spectral pyrometry system (36) configured to receive a broadband wavelength radiation signal (80) from a turbine component (56), for separating the broadband wavelength radiation signal (80) into multiple narrow wavelength band radiation signals (94), to determine the emissivity (122) of the turbine component (56), function of the narrow wavelength band radiation signals (94), and for detecting scaling (104) on a surface of the turbine component (56) as a function of the emissivity (122).

REFLECTIVE ELEMENTS AND DETECTORS COMPRISING OF THE REFLECTIVE ELEMENTS

UN PYROMETRE A RADIATION 1, OU AUTRE DETECTEUR OPTIQUE, A UN ENSEMBLE MIROIR 20 CAPABLE DE SUPPORTER DE HAUTES TEMPERATURES. L'ENSEMBLE MIROIR EST UN BLOC D'ACIER CONTENANT ENTRE 15 ET 20 DE CHROME, 4,0 ET 5,2 D'ALUMINIUM, 0,05 ET 0,4D'YTTRIUM, 0,2 ET 0,4 DE SILICONE ET ENTRE 0,00 ET 0,003 DE CARBONE. UNE SURFACE REFLECHISSANTE 24 SUR L'ENSEMBLE EST CONSTITUEE PAR UNE COUCHE D'OXYDE D'ALUMINIUM 27. L'ENSEMBLE EST FORME PAR CHAUFFAGE D'UN CORPS EN ACIER DE FACON A PRODUIRE LA COUCHE D'OXYDE D'ALUMINIUM QUI SERA ENSUITE POLIE JUSQU'A UN FINI REFLECHISSANT. APRES CHAUFFAGE, LE CORPS EST USINE A LA FORME DESIREE DE L'ENSEMBLE MIROIR. A RADIATION PYROMETER 1, OR OTHER OPTICAL DETECTOR, HAS A MIRROR ASSEMBLY 20 CAPABLE OF WITHSTANDING HIGH TEMPERATURES. THE MIRROR ASSEMBLY IS A BLOCK OF STEEL CONTAINING BETWEEN 15 AND 20 OF CHROME, 4.0 AND 5.2 OF ALUMINUM, 0.05 AND 0.4 OF YTTRIUM, 0.2 AND 0.4 OF SILICONE AND BETWEEN 0.00 AND 0.003 CARBON. A REFLECTIVE SURFACE 24 ON THE ASSEMBLY IS CONSTITUTED BY A LAYER OF ALUMINUM OXIDE 27. THE ASSEMBLY IS SHAPED BY HEATING A STEEL BODY SO AS TO PRODUCE THE LAYER OF ALUMINUM OXIDE WHICH WILL THEN BE POLISHED UP TO A REFLECTIVE FINISH. AFTER HEATING, THE BODY IS FACTORY TO THE DESIRED SHAPE OF THE MIRROR ASSEMBLY.

SELF VALIDATING GAS TURBINE ENGINE FLAME DETECTION SYSTEM USING DUEL OPTICAL VERIFICATION

A self validating flame detection system (10) for a turbine engine (12) configured to determine whether a flame exists in a turbine engine combustor (16) is disclosed. The self validating flame detection system (10) may include two different types of flame detection sensors (18) to reduce the risk of false positive signals. In at least one embodiment, the flame detection system (10) may include one or more infrared sensors (20) that sense infrared radiation within the combustor (16) of the turbine engine (12) and one or more ultraviolet light sensors (22) that sense ultraviolet light within the combustor (16) of the turbine engine (12). The flame detection system (10) may include a processor (24) configured to ignore the steady state infrared signal generated and instead analyze the dynamic infrared signal. The processor (24) may be configured to determine whether both types of sensors (18) indicate a flame out condition so that a false alarm does not occur.

MEASURING DEVICE HOUSING

The invention relates to a measuring device housing (10) for a sensor component, which detects a physical parameter without contact, comprising: a coupling apparatus (12) for supplying at least one flushing medium (22, 24, 26) and at least one signal transmission line in the housing interior, a guide pipe (14) arranged on the coupling apparatus (12) having a longitudinal axis (20) and a probe head (18) fastened on the end section (16) of the guide pipe (14), wherein the guide pipe (14) is designed to conduct or accommodate the at least one cooling medium (22, 24, 26) and the at least one signal transmission line up to the probe head (18). In order to provide a relatively compact and space-saving measuring device and thus also a measuring device housing (10), wherein different probe heads can be relatively easily and reliably transferred to different cooling media (22, 24, 26) conducted in the guide pipe (14), according to the invention the probe head (18) and the end section (16), relative ...

PYROMETERS

A pyrometer configured to sense thermal radiation within a volume (e.g., a turbomachine turbine or turbine engine) can include a photodiode configured to sense radiation at least within a desired infrared bandwidth and to output a photodiode signal, and an optical bandpass filter disposed in front of the photodiode to prevent radiation outside of the desired bandwidth from reaching the photodiode. The desired infrared bandwidth can be selected to be outside the absorption bands of one or more selected fluids such that the presence of one or more fluids (gasses) within the volume does not affect radiation that reaches the photodiode.

КОРПУС ИЗМЕРИТЕЛЬНОГО УСТРОЙСТВА

Изобретение относится к области измерительной техники и касается корпуса измерительного устройства. Корпус включает в себя соединительное устройство, направляющую трубу и головку зонда. Соединительное устройство предназначено для подвода охлаждающей и/или промывающей среды и провода для передачи сигнала во внутреннюю часть корпуса. Направляющая труба расположена в соединительном устройстве. Головка зонда закреплена с возможностью разъединения на конечном участке трубы, противоположном соединительному устройству. Направляющая труба выполнена с возможностью проводить к головке зонда охлаждающую среду и провод для передачи сигнала. Головка зонда и конечный участок трубы имеют радиальные проходы для передачи охлаждающей среды от конечного участка в головку зонда. Между головкой зонда и направляющей трубой образован кольцевой канал, через который подведенная по проходам направляющей трубы охлаждающая среда может подаваться через радиальные проходы головки зонда в ее внутреннюю часть. Технический ...

OPTISCHES STRAHLUNGSPYROMETER ZUM EINBAU IN EIN GASTURBINENTRIEBWERK

Motor vehicle turbocharger rotating turbine blade temperature sensor light guide receiver calibration procedure uses adjacent calibration surface with thermo sensor in static operating conditions

A rotating turbine (1) blade temperature sensor light guide receiver calibration procedure constructs a calibration curve by comparing thermographic heat radiation from an adjacent fixed calibration surface (8) in identical material using thermography (3) and a thermo sensor (14) temperature in static operating conditions : Independent claims are included for equipment using the procedure and for a subsidiary calibration step measuring the opacity of the optical window.

High temperature seal assembly for optical sensor

Optical Pyrometers

A remote pyrometer for sensing heat radiated from within a turbine guide vane

Use of an optical fibre for the direct receipt of heat radiation for transmission to a remote pyrometer is enabled by the provision of an apertured, contaminant free compartment in the component being heated, and aligning the heat receiving end of the optical fibre with the aperture so as to receive radiated heat from within the compartment. Heat is conducted through the walls of the compartment from a hot and hostile environment such as the interior of a gas turbine engine. The heat is then radiated from the internal walls of the compartment. In the embodiment of the invention the compartment comprises a hollow guide vane structure within the turbine.

REFLECTORS FOR USE AT HIGH TEMPERATURES

RADIATION-RESPONSIVE APPARATUS

RADIATION-DETECTING DEVICES

... 1503042 Detecting ultraviolet radiations SMITHS INDUSTRIES Ltd 21 May 1975 [21 May 1974] 22551/74 Heading G1A A radiation detector comprises a sensor 10 arranged to receive radiation via a gold film filter 16 carried by a window 15 at the end of a tubular guideway 14. The thickness of the gold film is substantially 100 Angstrom units to attentuate the infra-red to a greater extent than the ultraviolet radiations. The window 15 consists of a sapphire lens and the inside surface of the titanium tubular guideway 14 has a reflective coating 17 of silver or aluminium. A further reflective coating 18 also of silver or aluminium is provided on the outside of the gas-filled electrical-discharge tube 10 except at the domed end. Electrodes 19 are brazed to respective leads 20 which are coiled and rubber sheathed to withstand shock and vibration. The tube 10 may be replaced by a solid state sensor. The guideway may be a glass tube or a sapphire rod each with a reflective coating on its outer surface ...

Temperature sensor for a high speed rotating machine

FIBRE-OPTIC CABLE ASSEMBLIES AND RADIATION PYROMETERS

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

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

FIBRE-OPTIC CABLE ASSEMBLIES AND RADIATION PYROMETERS

In known pyrometers for gas-turbine engines, the temperature of different regions along the length of a turbine blade can be determined by focussing radiation from the blade with a lens onto a row of ends of several fibre-optic bundles. Arranging the ends of the bundles in a row does not, however, use the radiation focused by the lens very efficiently. In the present invention, the bundles are arranged in a jig with one bundle being positioned centrally and two other bundles of C-shape located on opposite sides and extending around the central bundle. In this way, the end of the three bundles forms a circular area with an efficient utilization of the radiation focus by the lens.

OPTICAL APPARATUS AND SIGHT TUBE FOR INSPECTING TURBINE ENGINE COMPONENTS

An apparatus for insertion through an opening in an outer casing of a gas turbine engine and inspection of internal turbine components at elevated temperatures having an optical sight tube configured to optically communicate with an interior of gas turbine engine via a distal end disposed at the interior and a proximal end disposed exterior of the internal turbine components and defined by a first longitudinal wall, at least one lens at the distal end of the optical sight tube adjacent to the longitudinal wall; and at least one longitudinal cooling groove in the longitudinal wall for flowing a cooling medium from a location external to the turbine to cool the optical sight tube at a location at least adjacent the distal end.

Multi-wavelength thermometer

Thermographic detection of internal passageway blockages

A method of thermal inspection of a component (100) defining at least one internal passageway (110, 120). The method includes receiving a continuous sequence of thermal images (712) of at least an exit hole (122) defined by the at least one internal passageway at a surface (102) of the component. The method also includes delivering a pressurized airflow pulse into the at least one internal passageway, receiving a temperature response signal (1000, 1000a, 1000b, 1000c) as function of time based on the received thermal images, determining a first derivative (1001, 1001a, 1001b, 1005) of the temperature response signal, and determining a level of blockage of the at least one internal passageway based on the first derivative of the temperature response signal.

APPAREIL DE TRANSMISSION D'UN RAYONNEMENT

L'INVENTION CONCERNE UN APPAREIL DE TRANSMISSION D'UN RAYONNEMENT COMPORTANT UNE FENETRE TRANSPARENTE, NOTAMMENT UN PYROMETRE, AGENCE DE MANIERE A EVITER DES SALISSURES SUR CETTE FENETRE. LE PYROMETRE COMPORTE UN TUBE INTERIEUR 18 RENFERMANT UNE LENTILLE 34 DANS SA PARTIE ARRIERE 43. UN DECROCHEMENT SEPARE CETTE PARTIE ARRIERE ET UNE PARTIE AVANT DE DIAMETRE REDUIT, OUVERTE A SON EXTREMITE. UN TUBE EXTERIEUR 15 DEFINIT AUTOUR DU TUBE INTERIEUR UN PASSAGE ANNULAIRE DE GAZ 45. IL COMPORTE A L'AVANT UNE OUVERTURE 47 QUI EST PLUS PETITE QUE LE DIAMETRE EXTERIEURDE LA PARTIE AVANT DU TUBE INTERIEUR ET PLUS LARGE QUE LE DIAMETRE INTERIEUR. DE L'AIR DE PURGE PENETRE PAR DES ORIFICES D'ENTREE 50 DANS LE PASSAGE 45 EN ARRIERE DE L'EXTREMITE DU TUBE INTERIEUR 18 ET S'ECOULE TRANSVERSALEMENT DEVANT CETTE EXTREMITE. UNE PRESSION SENSIBLEMENT CONSTANTE REGNE DANS LA PARTIE ARRIERE 43 DU TUBE ET EMPECHE L'ENTREE DE MATIERES CONTAMINANTES. L'INVENTION EST UTILISABLE DANS DES APPAREILS QUI RECOIVENT UN ...

TOGETHER OF JOINT HIGH TEMPERATURE FOR OPTICAL SENSOR HAS

Un ensemble de joint pour un capteur optique (30) utilisé dans un environnement à haute température est décrit qui comprend un tube de guidage (40) métallique oblong comportant une partie d'extrémité distale définissant une extrémité distale ouverte et une paroi arrière intérieure, une fenêtre en saphir (50) disposée à l'intérieur de la partie d'extrémité distale du tube de guidage métallique (40), la fenêtre en saphir (50) comportant une surface d'extrémité arrière prenant appui contre la paroi arrière intérieure de la partie d'extrémité distale du tube de guidage (40) métallique, et un manchon de montage (60) en platine pour fixer la fenêtre en saphir (50) au tube de guidage (40) métallique, le manchon de montage (60) en platine comportant une partie jointe au tube de guidage (40) métallique et une autre partie jointe à la fenêtre en saphir (50).

PYROMETER WITH SPATIAL RESOLUTION

The invention relates to a pyrometer for gas turbines, in which incident thermal radiation is split between a plurality of optical wave guides by means of a reflection prism and a lens according to regions on the surface of a turbine blade. The pyrometer can be built into the wall of the turbine without protruding and enables the simultaneous and parallel measurement of the temperature of a plurality of regions on the surface of the turbine blade when the spectrum of the heat radiation is largely maintained.

METHOD AND APPARATUS FOR DETECTING THE PRESENCE OF FLAME IN THE EXHAUST PATH OF A GAS TURBINE ENGINE

A method and apparatus for monitoring the exhaust path of a gas turbine engine for the presence of unwanted flames downstream from the main combustion chamber(s). The system is comprised of an Electro-Optics Module containing sensors and associated processing electronics as well as collection and transmitting optics, which relay the radiant energy generated by a flame event to the sensors. The information generated by the sensors is directly related to the time based intensity of the flame event, which can suggest problems associated with the condition of combustion related engine components. This information can then be used by the engine owner/operator to assess the condition of the engine and determine the more efficient required maintenance schedule.

Combined 2D and 3D nondestructive examination

An inspection apparatus (10) applying two dimensional nondestructive examination images onto a three dimensional solid model of a component (12) to display a virtual component (73) that may be manipulated to perform a nondestructive inspection. The two dimensional nondestructive examination images may be acquired from a plurality of views of the component in order to provide full coverage of the surface to be inspected, with appropriate stitching of images in regions of overlap between adjacent views. The two dimensional images (62) may be color or black and white photographs or ultraviolet or infrared images, for example. Multiple types of nondestructive examination images, results of inspection data evaluations, and design, operational and/or maintenance information may be displayed separately or jointly on the three dimensional solid model. Surface features of interest that are mapped as defined areas (76) on the three dimensional solid model may be displayed simultaneously in different ...

METHOD FOR MONITORING A HIGH-TEMPERATURE REGION OF INTEREST IN A TURBINE ENGINE

Устройство для определения температуры газовой среды в газотурбинных двигателях

Изобретение относится к области контактных измерений параметров высокотемпературных газов, в частности к средствам измерения температуры газа и распределения ее значений в полостях высокотемпературных элементов газотурбинных двигателей, и может быть применено для экспериментальных исследований рабочего процесса силовых установок при проведении аэродинамических испытаний. Устройство для определения температуры газовой среды в газотурбинных двигателях содержит размещенную в корпусе державку с приводом, установленные в державке основную и дополнительную термопары, подключенные через блоки регистрации термоЭДС к электронному сумматору, калибратор для термопар и источник теплового излучения для нагревания термопар, выполненный с возможностью размещения его в полости корпуса устройства, причем державка установлена в корпусе с возможностью вертикального перемещения, термоспаи основной и дополнительной термопар теплоизолированы между собой, а поверхностные слои термоспаев выполнены из материалов с разными коэффициентами поглощения. Устройство снабжено оптическим измерителем теплового излучения, имеющим объектив и поворотный привод и размещенным с противоположной стороны от источника теплового излучения относительно державки с термопарами, и теплоизолирующим экраном, установленным между измерителем теплового излучения и державкой с термопарами и имеющим измерительное отверстие, выполненное и расположенное таким образом, чтобы его площадь полностью затенялась термоспаями термопар, а калибратор для термопар выполнен в виде модели абсолютно черного тела с подогревателем и калиброванным отверстием, направленным в сторону объектива оптического измерителя теплового излучения. Технический результат – повышение точности получаемых результатов за счет исключения погрешности показаний термопар, связанных с опосредованным определением характеристик их термоспаев при определении температуры высокотемпературной газовой среды методом линейной экстраполяции. 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) ...

Thermisches Bildgebungssystem für eine Turbine

In einer Ausführungsform enthält ein System (10) ein Bildgebungssystem (36), das konfiguriert ist, um ein erstes Bild (108) einer umlaufenden Komponente (56) in einem Innenraum einer Turbine (18) unter Verwendung einer ersten Integrationszeit aufzunehmen, ein zweites Bild (110) der umlaufenden Komponente (56) in dem Innenraum der Turbine (18) unter Verwendung einer zweiten Integrationszeit, die sich von der ersten Integrationszeit unterscheidet, aufzunehmen und das erste Bild (108) von dem zweiten Bild (110) zu subtrahieren, um ein Differenzbild (112) zu erhalten.

UNSYMMETRISCHE LUFTSPÜLEINRICHTUNG ZUR REINIGUNG EINER LINSE.

Pyrometer mit Ortsauflösung

Optische Messeinrichtung zur Vermessung eines Objekts (6) in einer Fluss-Passage eines Fluids, wobei die Vermessung durch eine Wandung (1) der Fluss-Passage erfolgt, mit: einem Spiegelelement (3) zur Umlenkung von vom Objekt eintreffender Strahlung; wenigstens einem Abbildungselement (4) zur Fokussierung wenigstens eines Teils der Strahlung, so ausgestaltet, dass ein jeweiliger Bereich (8) von mehreren Bereichen auf der Oberfläche des Objekts (6) einem jeweiligen Ort von mehreren bestimmten Orten in der Messeinrichtung hinter dem Spiegel- und Abbildungselement (3, 4) in Richtung des Strahlungsverlaufs der Strahlung aus den jeweiligen Bereichen derart zugeordnet ist, dass die Strahlung aus den jeweiligen Bereichen (8) auf der Oberfläche des Objekts (6) an den Orten in der Messeinrichtung, die den jeweiligen Bereichen (8) zugeordnet sind, gleichzeitig detektierbar ist, wobei die Lage der jeweiligen Bereiche (8) und ihre Größe über das Spiegel- und das Abbildungselement (3, 4) sowie über den ...

Detecting the presence of flame in the exhaust path of a gas turbine

Apparatus for monitoring the exhaust path of a gas turbine engine for the presence of unwanted flames downstream from the main combustion chamber(s) comprises an Electro-Optics Module containing sensors and associated processing electronics as well as collection and transmitting optics, which relay the radiant energy generated by a flame event to the sensors. Light from the exhaust passes through a window, along optical fibers, to a refracting prism or diffraction grating, and thence to a sensor array. The sensor outputs are stored. The information generated by the sensors is directly related to the time based intensity of the flame event, which can suggest problems associated with the condition of combustion related engine components. This information can then be used by the engine owner/operator to assess the condition of the engine and determine the more efficient required maintenance schedule.

Optical probe

An optical probe (25) e.g. in a radiation pyrometer, for measurement of temperatures of blades (1) in a gas turbine has the objective end (39) of the probe (25) flush with the outer wall (13) of the turbine gas passage in order to avoid disturbance of the gas flow (5) and is thus angled away from the blade (1). The probe has an objective prism (31 ), e.g. of sapphire, whose front and rear faces (39, 40) are inclined with respect to each other, so that for rays of a preselected wavelength, the prism refracts into the probe only those rays from a preselected location (A) on the blade. A filter passes radiation at a single wavelength, and therefore a single image from the single preselected location (A) on the blade (1). An image centralising prism (33) realigns the optical path within the probe. ...

Improvements relating to the measurement of temperature

Temperature monitoring and/or measuring apparatus comprising radiation detector (9) and temperature probe 7 including at least one optical fibre 8 and radiation emitter 4 responsive to heat for the emission of radiation therefrom and located at the end of the optical fibre or fibres which convey the emitted radiation to the radiation detector. The fibre may be surrounded by cable 8 and the probe provided with a protective sheath. ...

Reflectors for use at high temperatures

A radiation pyrometer 1, or other optical sensor, has a mirror assembly 20 capable of withstanding high temperatures. The mirror assembly is a block of a steel containing between 15 and 20% chromium, 4.0 and 5.2% aluminium, 0.05 and 0.4% yttrium, 0.2 and 0.4% silicon, and 0.00 and 0.03% carbon. A reflective surface 24 on the assembly is provided by an aluminium oxide layer 27. The assembly is formed by heating a body of the steel such as to produce the aluminium oxide layer which is then polished to a reflective finish. After heating, the body is machined to the desired shape of the mirror assembly. ...

Thermal measurement system

Light emitted by object 12 and having a wavelength indicative of attenuation by optical sensor 22 is sensed and used in calculating gas temperature. The attenuation wavelength may be a wavelength where gas 16 absorbs and re-emits to match black-body emission with an effective emissivity of 1. In an aspect (Fig. 6), light emitted by the object and having a wavelength indicative of the object or gas temperature is sensed and used in calculating gas temperature. In an aspect (Fig. 5), light emitted by the object is filtered. Light having a wavelength associated with high gas absorption is sensed and used to calculate a first gas temperature. The object temperature is determined. A corresponding gas absorption parameter from a database is used to determine gas absorption. Actual gas temperature is calculated from the attenuation and the gas absorption. In an aspect, sensor 22 is at a predetermined distance from object 12, and comprises attenuation filter (52a, Fig. 2) associated with the attenuation ...

OPTICAL PYROMETER SIGHT TUBE ASSEMBLY FOR CONTROLLING A GAS TURBINE

FLAME DETECTION METHOD AND APPARATUS FOR GAS TURBINE EXHAUST PATH

A method and apparatus for monitoring gas turbine exhaust for unwanted flames employs a system comprising an electro-optics module (40), sensors (44), processing electronics (45), and collection and transmitting optics (20, 30). Information generated by the sensor can suggest problems with combustion related components.

ASYMMETRIC PURGE AIR SYSTEM FOR CLEANING A LENS

A purging air flow system for passing air over a lens to keep it clean and free from particulate contaminants and also for providing a positive flow of air away from the lens has baffles which cause a flow across the lens that is not symmetrical to avoid a dead air or stagnation zone in the center of the lens . The air supply used for such purging is controlled adequately so the flow changes direction and particles are removed from the main flow of purge air by inertial separation prior to the time the air contacts the lens . Such air entrained particles might otherwise deposit on the lens . A flow control orifice also may provide a secondary flow to carry the particles separated from the main flow out of the flow passageway .

MULTI-SPECTRAL PYROMETRY IMAGING SYSTEM

In one embodiment, a system (10) includes a turbine (18) including multiple components (52, 54, 58, 60, 62, 66, 70, 72) in fluid communication with a working fluid (46) that provides power or thrust. The system (10) also includes an imaging system (36) in optical communication with at least one component (52, 54, 58, 60, 62, 66, 70, 72). The imaging system (36) is configured to receive a broad wavelength band image (74) of the at least one component (52, 54, 58, 60, 62, 66, 70, 72) during operation of the turbine (18), to split the broad wavelength band image (74) into multiple narrow wavelength band images (90, 106, 122, 130, 136, 170, 172, 174, 176), and to output a signal indicative of a two-dimensional intensity map of each narrow wavelength band image (90, 106, 122, 130, 136, 170, 172, 174, 176).

APPARATUS AND METHOD FOR TEMPERATURE MAPPING A TURBINE COMPONENT IN A HIGH TEMPERATURE COMBUSTION ENVIRONMENT

Method and system for calibrating a thermal radiance map of a turbine component in a combustion environment. At least one spot (18) of material is disposed on a surface of the component. An infrared (IR) imager (14) is arranged so that the spot is within a field of view of the imager to acquire imaging data of the spot. A processor (30) is configured to process the imaging data to generate a sequence of images as a temperature of the combustion environment is increased. A monitor (42, 44) may be coupled to the processor to monitor the sequence of images of to determine an occurrence of a physical change of the spot as the temperature is increased. A calibration module (46) may be configured to assign a first temperature value to the surface of the turbine component when the occurrence of the physical change of the spot is determined.

WINDOW PURGING SYSTEM FOR A COMBUSTION INSTRUMENT

A purging air flow system that causes air to pass over a pyrometer lens or window (28) to keep it clean and free from particulate contaminants has an annular, continuous slot (50) for air inlet around the periphery of the lens (28) to permit flow of air across the lens (28) without any obstructions in the path of flow inwardly from the outer edge of the lens (28). An asymmetric flow pattern is established across the lens surface, either by having a differential size slot (50) at different peripheral portions of the peripheral edge of the lens or window (28), or by providing a radial swirl about the axis of the window (28) so that when the air goes through the slot (50), the tangential velocity creates a moving asymmetric flow pattern on the window surface (28A).

DEVICE AND DETECTOR RECEIVING SET OF RADIATIONS COMPRISING A FILTER

FAST BICHROMATIC PYROMETER HAS FIBEROPTIC

SYSTEM AND METHOD FOR PROVIDING SPECTRAL 2D TEMPERATURE

OPTICAL IMAGING SYSTEM FOR INSPECTING TURBINE ENGINE COMPONENTS AND METHOD FOR OPERATING SAME

A turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a camera located in the housing, a hollow probe extending from the housing and having a longitudinal axis, an image receiving device at an end of the hollow probe and communicably coupled with the camera, and method for operating same.

Airplane-Mounted External Fire Detection System

An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft forward of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft. 1. An aircraft-mounted external fire detection system comprising:optical circuitry mounted on an aircraft forward of an engine nacelle of the aircraft, the optical circuitry being configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum;processing circuitry communicatively coupled to the optical circuitry and configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.2. The aircraft-mounted external fire detection system of claim 1 , wherein to optically monitor the exterior of the engine nacelle claim 1 , the optical circuitry has a field of view comprising a perimeter substantially defined by a maximum expected deflection of the engine nacelle relative to the optical circuitry under maneuvering load of the aircraft such that the exterior of the engine nacelle remains within the field of view during the maneuvering load.3. The aircraft-mounted external fire detection system of claim 1 , wherein to transmit the warning to the operator terminal claim 1 , the processing circuitry is configured to control the operator terminal to display video of the engine nacelle.4. The aircraft-mounted ...

Dual infrared band apparatus and method for thermally mapping a component in a high temperature combustion environment

Apparatus and method for thermally mapping a component in a high temperature environment. An optical probe (10) has a field of view (14) arranged to encompass a surface of a component (15) to be mapped. The probe (10) captures infrared (IR) emissions in the near or mid IR band. An optical fiber (16) has a field of view to encompass a spot location (18) on the surface of the component within the field of view (14) of the probe (12). The fiber (16) captures emissions in the long IR band. The emissions in the long IR band are indicative of an emittance value at the spot location. This information may be used to calibrate a radiance map of the component generated from the emissions in the near or mid IR band and thus map the absolute temperature of the component regardless of whether the component includes a TBC.

GAS TURBINE ENGINE OPTICAL SYSTEM

A turbine engine optical system includes a plurality of viewing ports in an engine case that are circumferentially spaced from one-another. At least one optical device is optically coupled to the ports for viewing an internal chamber defined by the engine case and for depicting at least spatial temperature distributions. The chamber may be an exhaust chamber and the controller may have the capability to correlate events in the exhaust chamber to events in an upstream combustor chamber and may thereby adjust operating parameters of a fuel system of the combustor. 1. A turbine engine optical system comprising:a plurality of viewing ports in and circumferentially spaced about an engine case located downstream of a combustor section for depicting the spatial temperature distribution in an annular exhaust chamber defined between the engine case and an exhaust cone; andat least one optical device constructed and arranged to receive depictions through the plurality of viewing ports to detect at least exhaust temperature distributions.2. The turbine engine optical system set forth in further comprising:a controller for receiving an depiction input signal from the at least one optical device, analyzing the input signal, and outputting a control signal to control a parameter affecting combustion in a combustion chamber of the combustor section.3. The turbine engine optical system set forth in claim 2 , wherein the control signal controls a fuel pump of a fuel system.4. The turbine engine optical system set forth in claim 2 , wherein the control signal controls a fuel flow control valve of a fuel system.5. The turbine engine optical system set forth in claim 2 , wherein the control signal controls combustor air flow in a fuel-air mixer.6. The turbine engine optical system set forth in further comprising:a controller for receiving an depiction input signal from the at least one optical device, analyzing the input signal, and storing the data for future reference.7. The turbine ...

System and method for measuring temperature within a turbine system

A system (10) includes a radiation detector array (52) configured to direct a field of view (74) toward multiple conduits (60) within a fluid flow path from a turbine (16, 34) into a heat exchanger (26, 40). The radiation detector array (52) is configured to output a signal indicative of a multi-dimensional temperature profile of the fluid flow path based on thermal radiation emitted by the conduits (60). The system (10) also includes a controller (54) communicatively coupled to the radiation detector array (52). The controller (54) is configured to determine a temperature variation across the fluid flow path based on the signal, and to compare the temperature variation to a threshold value.

СПОСОБ МОНИТОРИНГА ИНТЕРЕСУЮЩЕЙ ВЫСОКОТЕМПЕРАТУРНОЙ ОБЛАСТИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

FIELD: measurement equipment. SUBSTANCE: invention relates to engine operation control and considers the method of monitoring of high-temperature area of gas-turbine engines. For implementation of the method in the stationary vane with internal cooling the monitoring ports are made. In the vane a distal end of the monitoring device is arranged. EFFECT: monitoring device is designed with a possibility of change of position in the stationary vane with reference to the longitudinal axis of the vane and functional connection with ports for providing a necessary field of view of the area under consideration. 20 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 551 479 C2 (51) МПК G01J 5/00 (2006.01) G01J 5/08 (2006.01) G01M 15/14 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2013123030/28, 19.10.2011 (24) Дата начала отсчета срока действия патента: 19.10.2011 Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): ЗОМБО, Пол, Дж. (US), ЛЕМЬЕ, Деннис, Х. (US), ХАТЧЕР, Клиффорд (US) 21.10.2010 US 61/405.377; 17.10.2011 US 13/274.766 R U (73) Патентообладатель(и): СИМЕНС ЭНЕРДЖИ, ИНК. (US) (43) Дата публикации заявки: 27.11.2014 Бюл. № 33 (56) Список документов, цитированных в отчете о поиске: GB 2358059 A, 11.07.2001. US 4037473 A1, 26.07.1977. US 7015473 B2, 21.03.2006. RU 1253262 C, 27.06.1995 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 21.05.2013 2 5 5 1 4 7 9 (45) Опубликовано: 27.05.2015 Бюл. № 15 2 5 5 1 4 7 9 R U US 2011/056884 (19.10.2011) C 2 C 2 (86) Заявка PCT: (87) Публикация заявки PCT: WO 2012/054602 (26.04.2012) Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) СПОСОБ МОНИТОРИНГА ИНТЕРЕСУЮЩЕЙ ВЫСОКОТЕМПЕРАТУРНОЙ ОБЛАСТИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (57) Реферат: Изобретение относится к области контроля для мониторинга. Прибор для мониторинга работы двигателей и касается способа выполнен с ...

Flame detection method and apparatus for gas turbine exhaust path

Radiation pyrometer

A radiation pyrometer has four rectangular photodiodes 21 to 24 mounted in an orthogonal array 20. Radiation from a hot body 2 is focussed as a circular image 25 centrally of the array. The outputs of diagonally opposite photodiodes 21 and 23, and 22 and 24 are connected together to form two identical output channels. The output of each channel is insensitive to displacement of the image 25' since the resulting decrease in coverage of one photodiode 22 (or 23) is compensated by the increase in coverage of the other photodiode 24 (or 21) of the pair. ...

Temperature sensor for a high speed rotating machine

An infrared temperature sensor system measures the emissivity of a surface, such as a rotor 101. An IR sensor 2 is positioned near or integral to a heating means, such as a heater (14, fig 2) or a motor 26. The IR sensor 2 is directed at the surface of an object such as a rotor shaft 100 and the temperature of the sensor 2 is raised by the heating means 26 without significantly heating the object surface 101. The voltage generated by the sensor 2 is compared with an expected voltage and determines whether the IR system is working at ideal operational status. This measurement can also enable calculating the emissivity of the surface 101 depending on an expected emissivity and the ratio of expected and generated voltages. The system is intended for use in a turbo-molecular vacuum pump rotor 100 to monitor potential thermal expansion of rotor blades 9 and therefore prevent failure.

Radiation pyrometer

A radiation pyrometer for indicating the temperature of the blades 5 of a gas-turbine engine 4 has four light guides in the form of heat- resistant sapphire rods 32 to 35 the forward ends of which are located close to one another in a row. A sapphire lens 21 focuses radiation emitted by the turbine blades onto the rods, the image plane 45 being tilted out of parallel with the lens so as to allow for the angle of the turbine blades. Each rod extends within a metal sheath 36 to 39, the forward ends of which are brazed into apertures in a metal plate 40 which lies in the image plane. At their rear ends, the sheaths are brazed into a metal plate 47, the sapphire rods being aligned and optically coupled with respective fibre-optic bundles 65 to 68. A small gap separates the forward end of each fibre-optic bundle from its respective rod, so as to allow for axial displacement of the rods relative to the fibre-optic bundles. The fibre-optic bundles are enclosed within a rubber sleeve 84 that extends ...

Radiation pyrometer

A radiation pyrometer has an inner tube with a lens mounted in a rear portion which is stepped to a forward portion of reduced diameter that is open at its forward end. An outer tube extends coaxially around the inner tube and is separated from it by an annular gas passage. The outer tube has an aperture at its forward end that is smaller that the external diameter of the forward end of the inner tube and larger than the internal diameter. The outer tube has gas inlets into the passage while are located rearwardly of the forward end of the inner tube, the area of the gas inlets being greater than the gap between the forward end of the inner tube and the outer tube. Gas flows through the inlets, along the passage, across the forward end of the inner tube and out the aperture, thereby setting up a substantially constant pressure in the rear portion of the inner tube and reducing the entry of contaminants.

RADIATION PYROMETER

PYROMETER APPARATUS

ELECTRO-OPTIC APPARATUS

OPTICAL DEVICES AND ENGINE INSTALLATIONS INCLUDING SUCH DEVICES

SYSTEM FOR MONITORING A HIGH-TEMPERATURE REGION OF INTEREST IN A TURBINE ENGINE

A system (8) for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The system includes an internally cooled stationary vane (12) located in a path of a working gas of the turbine. A monitoring port (14) is located in the stationary vane. A monitoring instrument (16) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.

SMART RADIATION THERMOMETRY SYSTEM FOR REAL TIME GAS TURBINE CONTROL AND PROGNOSIS

A smart radiation thermometry system including a turbine component is provided. The smart radiation thermometry system includes an optical imaging sub-system configured to receive a continuous broad wavelength band radiation signal emitted by the turbine component. The thermometry system also includes a wavelength splitting sub-system in optical communication with the optical transmission sub-system, wherein the wavelength splitting sub-system receives the continuous broad wavelength band radiation signal, and splits the radiation signal into multiple sub-wavelength band signals. The thermometry system further includes at least one detector array in optical communication with the wavelength-splitting sub-system, wherein the at least one detector array receives the multiple sub-wavelength band signals, and outputs respective analog voltage signals for each of the signals. The thermometry system further includes at least one high-speed multi-channel analog-to-digital converter (ADC) electrically ...

Multiwavelength thermometer

A thermal measurement system (10) comprises a light collection device (22); and a detection system (40, 140, 240, 340) in communication with the light collection device (22). The detection system (40, 140, 240, 340) is configured to detect light (94) intensity from a gas (80). The present invention has been described in terms of specific embodiment(s), and it is recognized that equivalents, alternatives, and modifications, aside from those expressly stated, are possible and within the scope of the appending claims.

HIGH-TEMPERATURE SEAL ASSEMBLY FOR OPTICAL SENSOR

SYSTEM FOR MONITORING A HIGH-TEMPERATURE REGION OF INTEREST IN A TURBINE ENGINE

A system (8) for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The system includes an internally cooled stationary vane (12) located in a path of a working gas of the turbine. A monitoring port (14) is located in the stationary vane. A monitoring instrument (16) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.

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

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

Thermal measurement system for fault detection within a power generation system

A system includes a radiation sensor configured to direct a field of view toward a conduit within a heat recovery steam generator, and to output a signal indicative of a temperature of the conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, and to compare the temperature to a threshold value.

Self validating gas turbine engine flame detection system using duel optical verification

A self validating flame detection system ( 10 ) for a turbine engine ( 12 ) configured to determine whether a flame exists in a turbine engine combustor is disclosed. The self validating flame detection system ( 10 ) may include two different types of flame detection sensors to reduce the risk of false positive signals. In at least one embodiment, the flame detection system ( 10 ) may include one or more infrared sensors ( 20 ) that sense infrared radiation within the combustor of the turbine engine ( 12 ) and one or more ultraviolet light sensors ( 22 ) that sense ultraviolet light within the combustor of the turbine engine ( 12 ). The flame detection system ( 10 ) may include a processor ( 24 ) configured to ignore the steady state infrared signal generated and instead analyze the dynamic infrared signal. The processor ( 24 ) may be configured to determine whether both types of sensors indicate a flame out condition so that a false alarm does not occur.

Turbine engine thermal imaging system

In one embodiment, a system includes an imaging system configured to capture a first image of a rotating component within an interior of a turbine using a first integration time, to capture a second image of the rotating component within the interior of the turbine using a second integration time, different than the first integration time, and to subtract the first image from the second image to obtain a differential image.

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 ...

IMAGE CONDUIT FOR FUEL NOZZLE ASSEMBLIES

A fuel nozzle for a gas turbine engine includes a feed arm including a fuel passage for issuing a spray of fuel. A nozzle assembly is fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage. A fiber optic cable is configured to collect burner radiation for a pyrometer input and has a first end centered within an optical connector of the nozzle assembly and a second end exposed from the spray outlet. The fiber optic cable fitted within the feed arm and nozzle assembly has a permanent bend radius preformed in the fiber optic cable. The bend radius can be equal to or greater than the minimum bend radii for the fiber optic cable to serve as a wave guide in wavelengths for monitoring combustion. 1. A fuel nozzle for a gas turbine engine , comprising:a feed arm including a fuel passage for issuing a spray of fuel;a nozzle assembly fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage; anda fiber optic cable configured to collect burner radiation for a pyrometer input having a first end centered within an optical connector of the nozzle assembly and a second end exposed from the spray outlet, wherein the fiber optic cable fitted within the feed arm and nozzle assembly has a permanent bend radius preformed in the fiber optic cable.2. The fuel nozzle of claim 1 , wherein the bend radius is equal to or greater than the minimum bend radii for the fiber optic cable to serve as a waveguide for wavelengths for monitoring combustion.3. The fuel nozzle of claim 2 , wherein the fiber optic cable includes a rigid metal sheath enclosing a plurality of individual wave guides.4. The fuel nozzle of claim 3 , wherein each wave guide is spaced apart from the other wave guides.5. The fuel nozzle of claim 3 , wherein interstitial sites between each wave guide are filled with compacted alumina powder.6. The fuel nozzle of claim 3 , wherein each wave guide is 0.017 inches in diameter such that ...

Temperature detecting device for a gas turbine power plant and gas turbine power plant comprising said temperature detecting device

A temperature detecting device for a gas turbine power plant is provided with at least one optical probe configured to detect a parameter indicative of a temperature and with at least one capsule configured to define a camera inside which the optical probe is housed.

Methods regarding optical probe having an inner tube with separable tube sections to house optical elements

In an optical probe ( 10 ) having an inner tube ( 30 ) arranged to house one or more optical elements ( 32 ), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections ( 32, 34 ) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections ( 32, 34 ) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.

Systems and methods for thermal imaging systems

A thermal imaging system for use in maintaining a turbine assembly includes a case, a single pixel detector positioned within the case, at least one optical transportation device, and a prism. The optical transportation device is coupled to the case and configured to direct electromagnetic radiation to the single pixel detector. The prism is coupled to the optical transportation device and configured to direct electromagnetic radiation into the optical transportation device and to the single pixel detector. At least the prism and the optical transportation device are inserted into the turbine assembly and the single pixel detector acquires images of the turbine assembly.

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 ...

Insulation Quality Indicator Module For A Valve And Actuator Monitoring System

The present application provides a method of evaluating insulation quality in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include casing temperatures and insulation temperatures, comparing the casing temperatures and the insulation temperatures to predetermined casing and insulation values, and altering one or more of the operating parameters and/or initiating repair procedures if the casing temperatures fall below the casing predetermined values and/or the insulation temperatures exceed the insulation predetermined values. 1. A method of evaluating insulation quality in a turbine by a data acquisition system , comprising:receiving a plurality of operating parameters from a plurality of sensors;wherein the plurality of operating parameters comprises casing temperatures and insulation temperatures;comparing the casing temperatures and the insulation temperatures to predetermined casing and insulation values; andaltering one or more of the plurality of operating parameters and/or initiating repair procedures if the casing temperatures fall below the casing predetermined values and/or the insulation temperatures exceed the insulation predetermined values.2. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises taking a valve out of service.3. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises repairing or replacing an insulation layer.4. The method of claim 1 , wherein the casing temperatures are determined by an inner wall casing temperature sensor and an outer wall casing temperature sensor.5. The method of claim 1 , wherein the plurality of operating parameters comprises a thermal gradient through the casing wall.6. The method of claim ...

SYSTEMS AND METHODS FOR PLANAR TEMPERATURE MEASUREMENT

Various embodiments include systems and apparatuses adapted for detecting two-dimensional turbomachine exhaust temperature. In some embodiments, a system includes a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine, a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid and at least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid. 1. A system comprising:a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine;a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid; andat least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid.2. The system of claim 1 , wherein the two-dimensional grid is adapted to rotate relative to a primary axis of the gas turbomachine claim 1 , ormove translationally along a primary axis of the gas turbomachine.3. The system of claim 1 , wherein the radiation detection device includes one of an infrared camera or a multi-color pyrometry system.4. The system of claim 1 , wherein the radiation detection device includes an optical system to collect ...

Automated Analytics Systems and Methods

An automated analytics system can include a sensor system that obtains measurement data by monitoring one or more parameters at each of a number of locations on each of a number of replicated components of an object. A computing device receives the measurement data from the sensor system and uses the measurement data to automatically generate a computerized representation of each of the plurality of replicated components. Thereafter, upon receipt of an input query, the computing device generates a synthesized representation of the object that is specifically directed to a parameter of interest indicated in the query. The synthesized representation may be displayed in a visual format that is interpretable by a human to derive information associated with the parameter of interest.

Self-cooled four-shaft turbine panoramic temperature measuring device

A four-shaft panoramic scanning temperature measuring device with a circulating water-cooling device is provided, which not only improves the working reliability of the probe, but also increases the overall flexibility and scanning measurement efficiency. The circulating water-cooling device is self-cooled. Compared with the conventional single-circulation water-cooling way, the design of five cooling cavities can achieve higher circulating water-cooling efficiency. The four-shaft structure includes a shaft structure for translation, a shaft structure for rotation, a shaft structure for swinging, and a shaft structure with coaxial sight pipe and light pipe. The design of the four-shaft structure is able to panoramically scan the high-temperature components inside the turbine. The temperature measuring device integrates functions of cooling, swinging, translating and rotating together, which solves problems of large size and complex control of the conventional temperature measuring device. 1the cooling device comprises water-cooling pipelines, a connecting plate, a mounting flange plate, a cooling stage and a cooling pond, wherein: the water-cooling pipelines are connected to the cooling stage; each of the water-cooling pipelines comprises an inlet pipe and an outlet pipe, and totally five water-cooling pipelines are arranged on one side of the cooling stage; one end of each water-cooling pipeline is connected to a cooling cavity of the cooling stage where cooling water is circulated; adjacent cooling cavities are separated with a separation column; the other end of each water-cooling pipeline is connected to the cooling pond; through the water-cooling pipelines, hot water in each cooling cavity is pumped into the cooling pond and cooled; the cooled water is pumped into each cooling cavity again to keep cooling the probe, so that a water-cooling circulation is formed for continuously cooling the probe; the cooling pond is separated into five independent parts which ...

Inspection system and method

An inspection system includes one or more processors and an infrared (IR) camera operably coupled to the one or more processors. The one or more processors control a microwave transmitter to sequentially emit microwaves having different frequencies within a designated frequency range into an object during a first sweep. The IR camera generates thermal image data of the object after the object is heated by each of the different frequencies of microwaves. The one or more processors analyze the thermal image data and determine a selected frequency within the designated frequency range that provides greater heating of the object than one or more other frequencies in the designated frequency range. The one or more processors also analyze select thermal image data of the object, responsive to heating of the object by the selected frequency of microwaves, to detect an element in the object.

SYSTEM AND METHOD FOR DETECTING ANOMALIES IN A COMPONENT

An inspection system for inspecting a component is presented. The inspection system includes a probe unit, wherein the probe unit includes a first flux concentrator operatively coupled to a first surface of the component. Also, the probe unit includes at least one inductive coil positioned around the first flux concentrator, and configured to induce an electrical current flow in at least a portion of the component via the first flux concentrator. Further, the inspection system includes an infrared (IR) camera configured to capture a plurality of frames corresponding to the portion of the component. In addition, the inspection system includes a processing unit electrically coupled to the IR camera and configured to determine an anomaly in the component based on the captured plurality of frames. 1. An inspection system for inspecting a component , the inspection system comprising: a first flux concentrator operatively coupled to a first surface of the component;', 'at least one inductive coil positioned around the first flux concentrator, and configured to induce an electrical current flow in at least a portion of the component via the first flux concentrator;, 'a probe unit, wherein the probe unit comprisesan infrared (IR) camera configured to capture a plurality of frames corresponding to the portion of the component; anda processing unit electrically coupled to the IR camera and configured to determine an anomaly in the component based on the captured plurality of frames.2. The inspection system of claim 1 , wherein the processing unit is configured to:construct a thermal image based on the captured plurality of frames; anddetermine presence of a thermal signature in the thermal image, wherein the thermal signature is representative of the anomaly in the component.3. The inspection system of claim 1 , wherein the first flux concentrator is disposed on or proximate to the first surface of the component.4. The inspection system of claim 1 , further comprising a power ...

METHOD OF INSPECTION FOR COOLING HOLES IN TURBINE AIRFOIL

An airfoil has an of internal cooling channel, and cooling holes extending from the internal cooling channel to an outer skin. Air is injected into the cooling channel, and then into an inlet of the cooling hole. The exit of the air from an outlet of the cooling hole at the outer skin is monitored to determine whether the outlet is blocked. A location of the inlet of the cooling hole is determined by utilizing the determined location of the outlet, in combination with a known angle through which the cooling hole extends. 1. A method of determining quality of manufacture of a component comprising the steps of:forming a component having an internal cooling channel, and cooling holes extending from said internal cooling channel to an outer skin of said component;injecting air into the internal cooling channel, and then into an inlet of said cooling hole, and then out of an outlet of said cooling hole and monitoring the exit of the air from the outlet at the outer skin to determine whether said outlet is blocked and determining the location of the outlet; anddetermining a location of the inlet of said cooling hole by utilizing the location of said outlet of said cooling hole, in combination with a known angle through which the cooling hole extends.2. The method as set forth in claim 1 , wherein said monitoring of the exit of air is performed by an infrared detector.3. The method as set forth in claim 2 , wherein a distance from the outer skin to the internal cooling channel is determined utilizing flash thermography.4. The method as set forth in claim 3 , wherein said distance is also used to determine the location of the inlet of said cooling hole.5. The method as set forth in claim 4 , wherein said component has an airfoil.6. The method as set forth in claim 5 , wherein said infrared detector is an infrared camera.7. The method as set forth in claim 6 , wherein said infrared camera is also a part of the flash thermography step.8. The method as set forth in claim 7 , ...

Multi-color pyrometry imaging system and method of operating the same

A multi-color pyrometry imaging system for a high-temperature asset includes at least one viewing port in optical communication with at least one high-temperature component of the high-temperature asset. The system also includes at least one camera device in optical communication with the at least one viewing port. The at least one camera device includes a camera enclosure and at least one camera aperture defined in the camera enclosure, The at least one camera aperture is in optical communication with the at least one viewing port. The at least one camera device also includes a multi-color filtering mechanism coupled to the enclosure. The multi-color filtering mechanism is configured to sequentially transmit photons within a first predetermined wavelength band and transmit photons within a second predetermined wavelength band that is different than the first predetermined wavelength band.

Flash thermography photobox

A system for automated condition assessment of a turbine component is provided. The system includes a partially enclosed photobox and a controller. The partially enclosed photobox includes a configurable rotational table adapted to carry the turbine component, at least one wall perpendicular to and abutting a horizontal platform upon which the rotational table is carried. The photobox also includes a plurality of cameras configured to be automatically positioned at locations surrounding the turbine component and capture images of the turbine component. The controller communicates with each of the cameras to respectively control the positioning of each camera in order to capture a desired view of the turbine component. At least one of the cameras is an infrared camera configured to perform flash thermography capturing a thermographic image of a portion of the turbine component. The thermographic image is used to assess the condition of the turbine component.

METHOD AND ASSEMBLY FOR MEASURING A GAS TEMPERATURE DISTRIBUTION IN A COMBUSTION CHAMBER

Provided is an optical sensor directed into a combustion chamber is used to selectively sense a predefined spectral range of an optical spectrum for different light paths running through the combustion chamber to measure a gas temperature distribution in the combustion chamber. A spectral intensity is determined for each spectral range and associated with an item of light path information which identifies the light path in question. The spectral intensities determined and and the associated items of light path information are fed as input data to a machine learning routine which is trained to reproduce spatially resolved training temperature distributions. Output data from the machine learning routine are then output as the gas temperature distribution. 1. A method for measuring a gas temperature distribution in a combustion chamber , whereina) in each case a specified spectral range of an optical spectrum is selectively captured for different light paths passing through the combustion chamber using an optical sensor that is directed into the combustion chamber.b) a respective spectral intensity is ascertained fora respective spectral range and assigned to a light path indication identifying the respective light path.c) the spectral intensities ascertained and the assigned light path indications are supplied as input data to a machine learning routine that is trained for a reproduction of spatially resolved training temperature distributions, andd) output data of the machine learning routine are output as gas temperature distribution.2. The method as claimed in claim 1 , wherein the machine learning routine utilizes at least one of a data-driven trainable regression model claim 1 , an artificial neural network claim 1 , a recurrent neural network claim 1 , a convolutional neural network. an autoencoder claim 1 , a deep learning architecture claim 1 , a support-vector machine claim 1 , a k-nearest neighbors classifier claim 1 , a physical model and-or a decision tree ...

LONG WAVE INFRARED SENSING FOR TURBOMACHINE

A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade. 1. A system , comprising:a turbomachine including one or more inspection ports; andan LWIR sensor positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component.2. The system of claim 1 , further comprising an imaging device operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy.3. The system of claim 1 , wherein the LWIR sensor is configured to image a compressor blade.4. The system of claim 1 , wherein the LWIR sensor is configured to image a ceramic coated turbine blade.5. The system of claim 4 , further comprising a determination system is configured to determine a condition of the coated turbine blade based on a thermal image comparison of the thermal image and a thermal template image.6. A method claim 4 , comprising:sensing thermal energy of a turbomachine component in an LWIR bandwidth.7. The method of claim 6 , further comprising converting the sensed thermal energy into a thermal image.8. The method of claim 7 , further comprising comparing the thermal image to a thermal template image to determine the health of the turbomachine component.9. The method of claim 8 , wherein the sensing step further includes sensing a ceramic coated turbine blade.10. The method of claim 9 , wherein the sensing step is performed while the turbomachine is activated and hot.11. The method of claim 10 , further comprising determining spots of material ...

THERMAL INSPECTION SYSTEM

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

MEASURING PROBE HEAD

A measuring probe head having a housing, which defines a receiving space and at least one coolant fluid supply channel fluidically connected thereto, and at least one sensor which is received, or is capable of being received, in the receiving space, wherein at least one partial region of the housing enclosing the receiving space has a porosity which defines a plurality of coolant fluid passage openings. 19.-. (canceled)10. A measuring-probe head , comprising:a housing, which defines an accommodating space and at least one cooling-fluid feed channel fluidically connected thereto, andat least one sensor, which is or can be accommodated in the accommodating space,wherein at least one sub-region which forms part of the housing, and encloses the accommodating space, has a porosity which defines a multiplicity of cooling-fluid through-passage openings, wherein the porosity-containing sub-region of the housing is produced by additive manufacturing.11. The measuring-probe head as claimed in claim 10 ,wherein the porosity of the sub-region of the housing is formed by a three-dimensional lattice structure.12. The measuring-probe head as claimed in claim 10 ,wherein at least the porosity-containing sub-region of the housing is produced from a metallic material.13. The measuring-probe head as claimed in claim 10 ,wherein the housing has at least two housing parts, which are connected to one another and of which one housing part forms the porosity-containing sub-region.14. The measuring-probe head as claimed in claim 10 ,wherein the pores have a pore size ranging from 50 μm to 3 mm.15. The measuring-probe head as claimed in claim 10 ,wherein cables of the at least one sensor are guided through the at least one cooling-fluid feed channel.16. A measuring method for sensing at least one measured value claim 10 , comprising:{'claim-ref': {'@idref': 'CLM-00010', 'claim 10'}, 'arranging the measuring-probe head as claimed in in a region of a turbomachine which has a working medium ...

SYSTEM AND METHOD FOR MONITORING OF GAS TURBINE COMPONENTS WITH INFRARED SYSTEM

An infrared imaging device includes a case, a plurality of electronic components, 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 case. The heat transfer structure is disposed within the case. The heat transfer structure is configured to conduct heat away from the plurality of electronic components. The heat transfer structure is further configured to regulate a temperature of the electronic components below the predetermined temperature parameter. 1. An infrared imaging device comprising:a case;a plurality of electronic components configured to collect data, said plurality of electronic components having a predetermined temperature parameter, said plurality of electronic components disposed within said case; anda heat transfer structure disposed within said case, said heat transfer structure configured to conduct heat away from said plurality of electronic components, wherein said heat transfer structure is further configured to regulate a temperature of said electronic components below the predetermined temperature parameter.2. The infrared imaging device in accordance with further comprising an insulation material claim 1 , said plurality of electronic components disposed within said insulation material.3. The infrared imaging device in accordance with claim 1 , wherein said heat transfer structure comprises a heat pipe and a plurality of fins coupled to said heat pipe.4. The infrared imaging device in accordance with claim 3 , wherein said heat pipe extends through said casing.5. The infrared imaging device in accordance with further comprising a phase change material claim 3 , said plurality of electronic components disposed within said phase change material claim 3 , said phase change material having a first material phase and a second material phase claim 3 , said phase change material configured to ...

APPARATUS AND METHOD FOR MONITORING AND QUANTIFYING PROGRESSION OF A STRUCTURAL ANOMALY IN A HIGH TEMPERATURE ENVIRONMENT OF A COMBUSTION TURBINE ENGINE

Apparatus and method for monitoring and quantifying progression of a structural anomaly, such as crack, over a surface of a component () in a high temperature environment of a combustion turbine engine The apparatus may include an electrically-insulating layer () formed at least over a portion of the surface of the component of the combustion turbine engine. At least a first detection leg () may be disposed on the electrically-insulating layer The first detection leg may be adapted to operate under a desired sensing modality from a bi-modal sensing scheme, such as may be implemented in one sensing modality by way of monitoring changes of an electrical parameter in an electrical circuit formed by the detection leg The sensing scheme may also be implemented by way of imaging radiance energy emitted by the detection leg 1. Apparatus for monitoring and quantifying progression of a structural anomaly over a surface of a component in a high temperature environment of a combustion turbine engine , the apparatus comprising:an electrically-insulating layer formed at least over a portion of the surface of the component of said combustion turbine engine; andat least a first detection leg disposed on the electrically-insulating layer, wherein the first detection leg is configured to operate under a desired sensing modality from a bi-modal sensing scheme available for monitoring and quantifying the progression of the structural anomaly2. The apparatus of claim 1 , wherein said at least first detection leg comprises an electrically-conductive material selected from platinum claim 1 , palladium and a nickel-chromium-based alloy3. The apparatus of claim 2 , wherein in a first sensing modality said at least first detection leg is electrically coupled to form an electrical circuit having an electrical parameter indicative of the progression of the structural anomaly4. The apparatus of claim 3 , wherein a physical characteristic of said at least first detection leg is chosen based on ...

HEAT FLUX MEASUREMENT SYSTEM

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

OPTICAL APPARATUS AND SIGHT TUBE FOR INSPECTING TURBINE ENGINE COMPONENTS

An apparatus for insertion through an opening in an outer casing of a gas turbine engine and inspection of internal turbine components at elevated temperatures having an optical sight tube configured to optically communicate with an interior of gas turbine engine via a distal end disposed at the interior and a proximal end disposed exterior of the internal turbine components and defined by a first longitudinal wall, at least one lens at the distal end of the optical sight tube adjacent to the longitudinal wall; and at least one longitudinal cooling groove in the longitudinal wall for flowing a cooling medium from a location external to the turbine to cool the optical sight tube at a location at least adjacent the distal end. 1. An apparatus for insertion through an opening in an outer casing of a turbine engine and inspection of internal turbine components at elevated temperatures comprising:an optical sight tube configured to optically communicate with an interior of gas turbine engine via a distal end disposed at the interior and a proximal end disposed exterior of the internal turbine components and defined by a first longitudinal wall;at least one lens at the distal end of the optical sight tube adjacent to the longitudinal wall; andat least one longitudinal cooling groove in the longitudinal wall for flowing a cooling medium from a location external to the turbine to cool the optical sight tube at a location at least adjacent the distal end.2. The apparatus of further comprising a plurality of holes in the longitudinal wall adjacent the lens to direct cooling medium from the at least one groove toward the lens to purge the lens.3. The apparatus of comprising a plurality of longitudinal cooling grooves.4. The apparatus of comprising a plurality of grooves in the at least one lens.5. The apparatus of further comprising a second longitudinal wall concentric to the first longitudinal wall.6. The apparatus of wherein the at least one longitudinal cooling groove is a ...

System and method for prognostic health monitoring of thermal barrier coatings

A system and method for prognostic health monitoring of thermal barrier coatings is provided. The system may comprise monitoring a thermal barrier coated gas turbine engine component, and measuring the infrared radiation emitting from the component. The measured thermal radiation data may be analyzed and compared to known material thermal radiation data in order to determine the health of the thermal barrier coating. The compiled comparison results may be compared against a historical statistical study to then determine the overall health of the thermal barrier coating. The system may comprise generating a health monitoring alert in response to the health of the thermal barrier coating indicating an imminent failure.

IMAGE CONDUIT FOR FUEL NOZZLE ASSEMBLIES

A fuel nozzle for a gas turbine engine includes a feed arm including a fuel passage for issuing a spray of fuel. A nozzle assembly is fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage. A fiber optic cable is configured to collect burner radiation for a pyrometer input and has a first end centered within an optical connector of the nozzle assembly and a second end exposed from the spray outlet. The fiber optic cable fitted within the feed arm and nozzle assembly has a permanent bend radius preformed in the fiber optic cable. The bend radius can be equal to or greater than the minimum bend radii for the fiber optic cable to serve as a wave guide in wavelengths for monitoring combustion. 111-. (canceled)12. A method of constructing a fiber optic cable for a fuel nozzle , the steps comprising:inserting seven wave guides into a metal sheath with alumina powder spaced apart from the other wave guides;drawing the metal sheath through a round reduction die to compress the alumina powder and fibers together;annealing the metal sheath; andforming at least one bend of a predetermined radius in the metal sheath by heating the metal sheath and applying a bending force,wherein the bend radius is formed so as not to exceed the minimum bend radius of the wave guides with respect to wavelengths for monitoring combustion,wherein each waveguide is 0.017 inches in diameter such that the metal sheath has minimum bend radius of three time a wave guide diameter.1314-. (canceled)15. The method of claim 12 , further comprising annealing the metal sheath again after the step of forming.16. The method of claim 12 , further comprising spacing each waveguide apart from the other waveguides.17. The method of claim 12 , further comprising filling interstitial sites between each waveguide with compacted alumina powder.18. The method of claim 12 , wherein forming the predetermined bend radius comprises forming the predetermined bend radius to ...

TEMPERATURE MEASURING SYSTEM

A temperature measuring system is disclosed herein. The temperature measuring system includes an optical assembly and a spectral data receiver. The temperature measuring system views passing gas and measures the radiant response of a selected gas. The measurement includes radiant intensities with respect to wavelengths in the infrared region. 1. A temperature measuring system for a gas turbine engine having a turbine with a turbine outer wall , a turbine inner wall , and rotor-stator axial gaps , comprising: a tip end disposed within the turbine; and', 'a fiber extending through the turbine outer wall, operable to receive an infrared light emitted from a gas and transmit the infrared light along its length; and, 'an optical assembly including'}a spectral data receiver disposed adjacent to the fiber opposite the tip end, operable to convert the received infrared light into a digital signal, the digital signal including and at least a first light intensity relative to a first wavelength band and a second light intensity relative to a second wavelength band.2. The temperature measuring system claim 1 , wherein the tip end is at least partially disposed within one of the rotor-stator axial gaps.3. The temperature measuring system claim 2 , wherein the tip end is at least partially oriented along a chord length that extends from a first point along the turbine inner wall across one of the rotor-stator axial gaps and to a second point along the turbine inner wall.4. The temperature measuring system claim 1 , wherein the fiber is shaped to face along a chord length that extends from a first point along turbine inner wall across one of the rotor-stator axial gaps and to a second point along the turbine inner wall.5. The temperature measuring system of claim 1 , wherein the gas is water vapor.6. The temperature measuring system of claim 1 , wherein the fiber is in fluid communication with the gas.7. A method for measuring temperature of a gas produced within a turbine during ...

SYSTEM AND METHOD FOR CONTROLLING ICE FORMATION ON GAS TURBINE INLET GUIDE VANES

Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency. 1. A method for detecting and alleviating ice formation on inlet guide vanes of a gas turbine , comprising:viewing a gas turbine inlet guide vane with an infra-red camera;actively monitoring emissivity intensity of the inlet guide vane with the infra-red camera;detecting when monitored emissivity is indicative of ice formation on the inlet guide vane; andalleviating the detected ice formation by altering intake airflow properties into the gas turbine.2. The method of claim 1 , the viewing step performed by placing the infra-red camera external the gas turbine and viewing the inlet guide vane through a viewing window formed in a housing of the gas turbine.3. The method of claim 1 , the infra-red camera comprising a micro bolometer detector in which detector electrical conductivity changes in response to temperature changes.4. The method of claim 1 , the monitored emissivity ice formation indication comprising viewed inlet guide vane aggregate emissivity intensity dropping below a defined threshold.5. The method of claim 1 , the monitored emissivity ice formation indication comprising a defined percentage of viewed inlet guide vane having ...

Optical imaging system for a gas turbine engine

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

METHOD AND SYSTEM FOR GAS TEMPERATURE MEASUREMENT

A temperature measurement system includes at least one temperature measurement probe. The at least one temperature measurement probe includes at least one hollow filament configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one hollow filament. The at least one hollow filament has a first diameter and a first emissivity. The at least one temperature measurement probe also includes at least one thin filament extending within at least a portion of the at least one hollow filament. The at least one thin filament is configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of the at least one thin filament. The at least one thin filament has a second emissivity and a second diameter less than the first diameter. 1. A temperature measurement system comprising: at least one hollow filament configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of said at least one hollow filament, said at least one hollow filament having a first diameter and a first emissivity; and', 'at least one thin filament extending within at least a portion of said at least one hollow filament, said at least one thin filament configured to emit thermal radiation in a predetermined and substantially continuous wavelength band at least partially representative of a temperature of said at least one thin filament, said at least one thin filament having a second emissivity and a second diameter less than the first diameter., 'at least one temperature measurement probe comprising2. The temperature measurement system in accordance with claim 1 , wherein said at least one thin filament and said at least one hollow filament comprise at least one of silicon carbide claim 1 , sapphire claim 1 , fused silica ...

SYSTEM AND METHOD FOR ON-LINE OPTICAL MONITORING AND CONTROL OF A GAS TURBINE ENGINE

A system for on-line optical monitoring of a gas turbine engine includes a viewport into a combustor of the gas turbine engine and an optical filter optically coupled to the viewport. The optical filter is configured to receive broad wavelength band thermal radiation from an interior surface of the combustor while the gas turbine engine is in operation, to substantially block wavelengths of the broad wavelength band thermal radiation emitted and/or absorbed by a flame and/or by exhaust gas within the combustor, and to output narrow wavelength band thermal radiation from the interior surface of the combustor. The system also includes a detector array in optical communication with the optical filter. The detector array is configured to receive the narrow wavelength band thermal radiation and to output signals indicative of a two-dimensional intensity map of the narrow wavelength band thermal radiation. 1. A system for on-line optical monitoring of a gas turbine engine , comprising:a viewport into a combustor of the gas turbine engine;an optical filter optically coupled to the viewport, wherein the optical filter is configured to receive broad wavelength band thermal radiation from an interior surface of the combustor while the gas turbine engine is in operation, to substantially block wavelengths of the broad wavelength band thermal radiation emitted, absorbed, or a combination thereof, by a flame, by exhaust gas, or a combination thereof, within the combustor, and to output narrow wavelength band thermal radiation from the interior surface of the combustor; anda detector array in optical communication with the optical filter, wherein the detector array is configured to receive the narrow wavelength band thermal radiation and to output signals indicative of a two-dimensional intensity map of the narrow wavelength band thermal radiation.2. The system of claim 1 , comprising a controller communicatively coupled to the detector array claim 1 , wherein the controller is ...

EVALUATION METHOD AND SYTEM FOR A LIGHTNING PROTECTION SYSTEM OF A WIND TURBINE COMPRISING A PLURALITY OF BLADES MADE OF CARBON FIBER REINFORCED PLASTIC OR POLYMER

Evaluation method for a lightning protection system of a wind turbine with blades (P), the lightning protection system comprising a down conductor connected to earth and to each blade (P) by means of conductor plates () embedded in the corresponding blade (P). The method is configured for determining the quality of the connections between the conductor plates () and the blade (P) thereof and comprises injecting direct current (I) between two conductor plates () of one and the same blade (P), a flow of current being generated through the segment of the blade (P) comprised between both conductor plates (), measuring the voltage (V) at measurement points (Pm) of said segment, comparing the voltages (V) to one another, and determining the quality of the connections between said conductor plates () and said blade (P) depending on the result of said comparison. Associated evaluation system. 1100121212. Evaluation method for a lightning protection system of a wind turbine () comprising a plurality of blades (P) made of carbon fiber reinforced plastic or polymer , the lightning protection system comprising a down conductor connected to earth and to each blade (P) by means of a plurality of conductor plates ( , ) that are embedded in the corresponding blade (P) , that are longitudinally distributed in said blade (P) , each conductor plate ( , ) extending along the entire width of said blade (P) , wherein the evaluation method is configured for determining the quality of the connections between the conductor plates ( , ) and the corresponding blade (P) and comprises the following successive steps:{'b': 1', '2', '1', '2, 'injecting direct current (I) between two conductor plates (, ) of one and the same blade (P), a flow of current being generated through the segment of the blade (P) comprised between both conductor plates (, ),'}measuring the voltage (V) with respect to a certain common reference point (Pref) at a plurality of surface measurement points (Pm) of said segment ...

Laser thermography

A non-destructive method for condition assessment of a turbine component is provided. The method includes providing a laser generating a light pulse that heats the turbine component. An infrared image is then captured of the heated turbine component. An analysis of the turbine component for a particular characteristic of the turbine component may then be done. A system for the non-destructive condition assessment of a turbine component is also provided.

DUAL INFRARED BAND APPARATUS AND METHOD FOR THERMALLY MAPPING A COMPONENT IN A HIGH TEMPERATURE COMBUSTION ENVIRONMENT

Apparatus and method for thermally mapping a component in a high temperature environment. An optical probe () has a field of view () arranged to encompass a surface of a component () to be mapped. The probe () captures infrared (IR) emissions in the near or mid IR band. An optical fiber () has a field of view to encompass a spot location () on the surface of the component within the field of view () of the probe (). The fiber () captures emissions in the long IR band. The emissions in the long IR band are indicative of an emittance value at the spot location. This information may be used to calibrate a radiance map of the component generated from the emissions in the near or mid IR band and thus map the absolute temperature of the component regardless of whether the component includes a TBC. 1. An apparatus comprising:an optical probe housed in a viewing tube, the optical probe having a field of view arranged to encompass a surface of a component to be thermally mapped in a high temperature combustion environment of a turbine engine, the optical probe effective to capture infrared (IR) emissions comprising a first band in an IR spectrum, wherein the first band in the IR spectrum comprises a near IR wavelength or comprises a mid IR wavelength, wherein the component of the turbine engine comprises a thermal barrier coating (TBC) subject to emittance variation in the combustion environment of the turbine engine; andan optical fiber housed in the viewing tube, a field of view of the optical fiber arranged to encompass a spot location on the surface of the component disposed within the field of view of the optical probe, the optical fiber effective to capture IR emissions comprising a second band in the IR spectrum, wherein the second band in the IR spectrum comprises a long IR wavelength effective to measure with a higher degree of accuracy emittance values from the TBC than the wavelengths in the first band, the IR emissions in the second band in the IR spectrum ...

Device for measuring temperature of turbine wheel in turbocharger and engine control method using temperature measurement device for turbine wheel

A device for measuring temperature of a turbine wheel in a turbocharger includes: a guide that passes infrared ray generated from the turbine wheel and includes a coolant path; a protection unit that protects an optical head which senses the infrared ray; and a signal processing unit that measures a temperature of the turbine wheel by processing a signal corresponding to the sensed infrared ray.

Temperature estimation method of high temperature member, content estimation method of tetragonal-prime phase, and deterioration determination method

A temperature estimation method includes the steps of measuring a content of a tetragonal-prime phase included in a coating layer formed on a surface of a high temperature member by X-ray diffraction or Rietveld analysis, Raman spectroscopy, or the like; and estimating a surface temperature of the high temperature member based on the estimated content of the tetragonal-prime phase.

THERMO-MECHANICAL FATIGUE SYSTEM FOR STATIC COMPONENTS

According to an aspect of this disclosure, a system of applying thermal loads may include at least one laser module, and a plurality of optical components fixed to the at least one laser module and directing a plurality of laser beams from the plurality of optical components towards a surface. Further, the plurality of laser beams apply radiative heating to the surface in accordance with the system. The system also includes at least one infrared camera measuring thermal conditions of the surface, and a controller coordinating operation of the at least one laser module and the at least one infrared camera. 1. A system of applying thermal loads , comprising:at least one laser module; 'wherein the plurality of laser beams apply radiative heating to the surface;', 'a plurality of optical components fixed to the at least one laser module and directing a plurality of laser beams from the plurality of optical components towards a surface;'}at least one infrared camera measuring thermal conditions of the surface; anda controller coordinating operation of the at least one laser module and the at least one infrared camera.2. The system of claim 1 , wherein the controller turns off the at least one laser module when the at least one infrared camera measures the thermal conditions of the surface.3. The system of claim 2 , wherein the surface is on a component of a gas turbine engine and thermal conditions of the surface are cycled.4. The system of claim 1 , wherein the plurality of optical components direct the plurality of laser beams towards the surface according to a pattern mapped across the surface.5. The system of claim 4 , wherein the pattern is a three-dimensional pattern of loci on the surface.6. The system of claim 5 , wherein the three-dimensional pattern of loci on the surface corresponds to the plurality of laser beams.7. The system of claim 6 , wherein a plurality of optical waveguides correspond to the plurality of optical components; andwherein the plurality of ...

FLASH THERMOGRAPHY DOUBLE WALL THICKNESS MEASUREMENT

A method of determining the thickness of an internal wall in a gas turbine engine component includes the steps of utilizing flash thermography to measure a complete thickness of a component between an outer wall and at least one enlarged cooling channel at a location where an outer cooling channel is positioned between the outer wall and the at least one enlarged cooling channel and where at least one member spans the cooling channel, such that the thickness is through the member which spans the outer cooling channel. An outer thickness of the component is measured from the outer wall to an outer wall of the outer cooling channel. A thickness is determined from an inner wall of the outer cooling channel to the at least one enlarged cooling channel by subtracting the measured outer thickness from the complete thickness, and also subtracting a known thickness of the outer cooling channel. 1. A method of determining the thickness of an internal wall in a gas turbine engine component comprising the steps of:(a) utilizing flash thermography to measure a complete thickness of a component between an outer wall and at least one enlarged cooling channel at a location where an outer cooling channel is positioned between said outer wall and the at least one enlarged cooling channel and where at least one member spans said outer cooling channel, such that said thickness is through said member which spans said outer cooling channel; and(b) measuring an outer thickness of said component from said outer wall to an outer wall of said outer cooling channel, and determining a thickness from an inner wall of said outer cooling channel to said at least one enlarged cooling channel by subtracting said measured outer thickness from said complete thickness, and also subtracting a known thickness of said outer cooling channel.2. The method as set forth in claim 1 , wherein a high emissivity outer layer is provided on said outer wall prior to said flash thermography.3. The method as set ...

Apparatus and Method for Analyzing Relative Outward Flow Characterizations of Fabricated Features

An apparatus and method for characterizing gas flow through features fabricated in a hollow part. A pressure regulated cooled gas is applied to an interior of the part to the features fabricated in the part. At the same time, a pressure regulated heated gas is applied to an exterior part skin; and the heated gas has a controlled temperature differential from the pressure regulated cooled gas applied to the part interior. An infrared signature of escaping gas and the surrounding part skin is analyzed by a classification method to identify acceptable and unacceptable fabricated features.

Flash thermography borescope

본 발명은 터빈 내부에 로케이팅된 복수의 회전 터빈 컴포넌트들 각각의 적외선 이미지를 생성하기 위한 플래시 서모그래피 디바이스에 관한 것이다. 디바이스는 각각의 컴포넌트에 의해 방사되는 열 에너지를 검출하기 위한 적외선 센서를 포함한다. 디바이스는 또한 보어스코프를 포함하며, 보어스코프는 보어스코프의 길이방향 축 상에 로케이팅된 뷰잉 단부를 갖는다. 보어스코프는, 적어도 하나의 컴포넌트가 뷰잉 단부의 시야 내에 있도록 뷰잉 단부를 터빈 내부에 로케이팅시키기 위해 검사 포트 내에 포지셔닝된다. 게다가, 디바이스는 회전자의 단일 회전 동안에 회전하는 컴포넌트들의 개수에 대응하는 복수의 광 펄스들을 생성하는 플래시 소스를 포함하며, 광 펄스들은 길이방향을 실질적으로 가로질러 배향된다. 각각의 컴포넌트로부터 방사되는 열 에너지는 보어스코프를 통해 적외선 센서에 전달되어 적외선 이미지들의 생성을 가능하게 한다. The present invention relates to a flash thermography device for generating an infrared image of each of a plurality of rotating turbine components located within a turbine. The device includes an infrared sensor for detecting the thermal energy radiated by each component. The device also includes a borescope, the borescope having a viewing end located on the longitudinal axis of the borescope. The borescope is positioned within the inspection port to locate the viewing end inside the turbine such that at least one component is within the view of the viewing end. In addition, the device includes a flash source that generates a plurality of light pulses corresponding to the number of rotating components during a single rotation of the rotor, the light pulses being oriented substantially across the longitudinal direction. The thermal energy radiated from each component is transferred to the infrared sensor through the borescope to enable the generation of infrared images.

One kind is directed to turbo blade infra-red radiation optical acquisition device

该发明公开了一种针对涡轮叶片红外辐射光采集装置，属于机械结构领域，具体设计光线的调焦方法。通过反射镜采集涡轮叶片表面的红外辐射光，通过准直镜准直，再通过聚焦镜最后由接收器采集，准直镜设置于准直滑块上，准直滑块设置于准直导轨上，准直滑块和准直导轨之间采用刚性小球来实现滑动连接，通过齿轮和齿条的啮合实现准直滑块的精确移动，为了是准直滑块的移动距离更加精确，在准直导轨上设置位置检测点，用于准直滑块的位置检测和校正；从而本发明具有涡轮叶片红外辐射光线采集相应，聚焦精度高的优点。

Optical device and inspection tube for inspecting turbine engine components

本发明提供一种用于从燃气涡轮发动机外壳中的开口插入并且在高温下检查内部涡轮部件的设备，所述设备具有：光学观察管，所述光学观察管配置成通过设置在燃气涡轮发动机内部的远端以及设置在所述内部涡轮部件外部并且由第一纵向壁限定的近端与所述内部进行光通信；至少一个透镜，所述至少一个透镜位于与所述纵向壁相邻的所述光观察管的所述远端；以及至少一个纵向冷却槽，所述纵向冷却槽位于所述纵向壁内，用于使得冷却介质从所述涡轮外部的位置流动，以在至少与所述远端相邻的位置冷却所述光学观察管。

System and method for monitoring of gas turbine components with infrared system

An infrared imaging device includes a case, a plurality of electronic components, 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 case. The heat transfer structure is disposed within the case. The heat transfer structure is configured to conduct heat away from the plurality of electronic components. The heat transfer structure is further configured to regulate a temperature of the electronic components below the predetermined temperature parameter.

System and method for disposable infrared imaging system

An infrared 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.

Methods regarding optical probe having an inner tube with separable tube sections to house optical elements

In an optical probe ( 10 ) having an inner tube ( 30 ) arranged to house one or more optical elements ( 32 ), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections ( 32, 34 ) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections ( 32, 34 ) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.

Optical apparatus and sight tube for inspecting turbine engine components

An apparatus 300 for insertion through an opening in an outer casing of a gas turbine engine and inspection of internal turbine components at elevated temperatures having an optical sight tube 302 configured to optically communicate with an interior of gas turbine engine via a distal end 303 disposed at the interior and a proximal end 305 disposed exterior of the internal turbine components and defined by a first longitudinal wall 318, at least one lens 310 at the distal end 303 of the optical sight tube 302 adjacent to the longitudinal wall 318; and at least one longitudinal cooling groove 316 in the longitudinal wall 318 for flowing a cooling medium 304 from a location external to the turbine to cool the optical sight tube 302 at a location at least adjacent the distal end 303.

RADIATION TRANSMISSION APPARATUS

OPTICAL TEMPERATURE SENSOR.

OPTICAL ELEMENT FOR PYROMETRIC MEASUREMENTS

Patent FR2093399A5

SYSTEM AND METHOD FOR THERMALLY INSPECTING OBJECTS

Un système de mesure thermique d'un objet (10) est fourni. Le système (10) comporte une matrice de détecteurs (56) bidimensionnelle, configurée pour recevoir un rayonnement dans des plages de longueurs d'onde multiples, la matrice de détecteurs (56) ayant un premier axe (124) représentant la dimension spatiale et un deuxième axe (126) représentant la dimension en longueur d'onde. Le système comporte également un système optique (50) configuré pour focaliser sur la matrice de détecteurs (56) le rayonnement émis par l'objet (10). A thermal measurement system of an object (10) is provided. The system (10) includes a two-dimensional detector array (56) configured to receive radiation in multiple wavelength ranges, the detector array (56) having a first axis (124) representing the spatial dimension and a second axis (126) representing the wavelength dimension. The system also includes an optical system (50) configured to focus the radiation emitted by the object (10) on the array of detectors (56).

Patent IN165153B

Four-shaft type multifunctional turbine blade temperature measuring device

本发明公开了一种四轴式多功能涡轮叶片测温装置，属于航空发动机领域，特别是含有四轴的多功能可自主冷却的涡轮叶片测温装置。解决目前的涡轮叶片的温度测量装置效率低、功能单一等问题。本发明提出四轴式测温装置，提高测温装置的整体灵活性,所述四轴式结构包括伸缩的轴式结构，旋转的轴式结构，摆扫的轴式结构，以及视管、光管同轴的轴式结构；摆扫、伸缩、旋转、冷却功能集成为一体式装置结果紧凑，克服了传统测温装置过大、控制复杂等难题；红外探测器的使用使装置可用于探测不同目标表面的温度。

Multiwavelength pyrometry systems

A thermal measurement system includes a number of detectors configured to receive radiation within respective wavelength ranges. The system also includes a mirror configured to selectively direct the radiation from an object to each of the detectors. The system further includes an actuator mechanically coupled to the mirror and configured to rotate the mirror through a number of angles. The system also includes an optical and probe subsystem disposed between the object and the mirror to focus the radiation on to the mirror.

Optical probe

An optical probe is particularly for use as part of the viewing system of a radiation pyrometer, e.g. for measurement of temperatures of turbine blades in a gas turbine aeroengine. Although the objective end of the probe lies flush with the outer wall of the turbine gas passage in order to avoid disturbance of the gas flow and is angled away from the blade by virtue of its conformity with the geometry of the outer wall of the gas passage, the probe's field of view nevertheless includes locations on the turbine blades which are considerably axially upstream from the probe's position. This is achieved by providing the probe with an objective prism whose front and rear faces are inclined with respect to each other, so that, for rays of a preselected wavelength, the prism refracts into the probe and along the internal optical path of the probe only those rays from a preselected location on the blade. Since the blade radiates at a number of wavelengths, a filter is included in the viewing system so that the pyrometer is presented with radiation at a single wavelength, and therefore with a single image from the single preselected location on the blade. The probe also includes an image centralizing prism in order to centralize the optical path within the probe, and glare stops in order to collimate the rays after they have passed through the objective prism and the image centralizing prism. The objective prism may be made of sapphire in order to withstand the heat of the turbine gases.

MULTISPECTRAL SYSTEM AND METHOD FOR PRODUCING 2D TEMPERATURE DATA

Système comprenant un système d'imagerie (36) conçu pour recevoir, d'un intérieur d'une turbine, une image de gaz (80) et d'une surface observable à travers les gaz (80), diviser l'image en une première carte 2D d'intensité de longueurs d'onde indiquant une température des gaz (80) et une deuxième carte 2D d'intensité de longueurs d'onde indiquant une température de la surface, et délivrer des signaux indiquant les première et deuxième cartes 2D d'intensité. A system comprising an imaging system (36) adapted to receive a gas image (80) and an observable surface through the gases (80) from a turbine interior, divide the image into a first wavelength intensity 2D map indicating a temperature of the gases (80) and a second wavelength intensity 2D map indicating a temperature of the surface, and outputting signals indicative of the first and second 2D maps intensity.

System and method for on-line optical monitoring within a gas turbine combustor section

온 라인 광학 검사 및 감시 시스템은 연소기 하우징 내에 존재하는 맨 웨이 보수용 출입 통로 외부에 장착된다. 광학 윈도우를 가지는 대체 맨 웨이 덮개는 연소기 하우징에 장착된다. 하나 또는 그 초과의 광학 카메라들은, 카메라 시야(FOV; field of view)가 맨 웨이 덮개 광학 윈도우를 통하여 지향되도록, 배향된다. 카메라 FOV는 자동화 움직임 제어 시스템의 제어 하에서와 같이, 연소 섹션 내의 복수 위치들로 이동하고, 영상들이 캡처된다. 다수의 영상들은 연소 섹션 내의 전체 병진 운동에 대한 영상을 포함할 수 있는, 합성 영상을 형성하도록 조합된다. 비주얼 영상 및/또는 적외선(IR; infrared) 열적 영상이 캡처될 수 있다. 열적 영상 정보는 컴포넌트 온도와 상관된다. 영상 정보는 영상화 컴포넌트들의 진동 특성들을 판단하기 위해 이용된다. An on-line optical inspection and monitoring system is mounted outside the manway maintenance access aisle within the combustor housing. An alternative manway cover with an optical window is mounted on the combustor housing. One or more optical cameras are oriented such that the camera field of view (FOV) is directed through the manway cover optical window. The camera FOV moves to multiple locations in the combustion section, as under the control of the automated motion control system, and images are captured. Multiple images are combined to form a composite image, which may include images of the entire translational motion within the combustion section. A visual image and/or an infrared (IR) thermal image may be captured. Thermal imaging information is correlated with component temperature. Image information is used to determine vibration characteristics of imaging components.

Method for determining a thermal history of a component

The present invention generally relates to a method for determining the thermal history of a component by means of a detection material applied on such component, the detection material having a colour responsive to an outer temperature. This invention allows automated evaluation of test results and identification of appropriate temperatures. The proposed method provides higher repeatability of results and ensures independence of results from external factors.

System for monitoring a high-temperature region of interest in a turbine engine

A system ( 8 ) for monitoring a high-temperature region of interest in a turbine engine ( 10 ) is provided. The system includes an internally cooled stationary vane ( 12 ) located in a path of a working gas of the turbine. A monitoring port ( 14 ) is located in the stationary vane. A monitoring instrument ( 16 ) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.

OPTICAL CABLE, PYROMETER COMPRISING SUCH A CABLE AND METHOD OF MANUFACTURING THE CABLE

L'INVENTION CONCERNE UN CABLE OPTIQUE 1 COMPORTANT PLUSIEURS FAISCEAUX DISTINCTS 11, 12, 13 DE FIBRES OPTIQUES ET UTILISEES NOTAMMENT DANS UN PYROMETRE A RAYONNEMENT. A UNE PREMIERE EXTREMITE 2 DU CABLE, LES FAISCEAUX SONT DISPOSES DANS UN GABARIT 21. L'UN DES FAISCEAUX EST DISPOSE AU CENTRE, TANDIS QUE LES AUTRES FAISCEAUX PRESENTENT UNE SECTION EN FORME DE C ET SONT DISPOSES LE LONG DES COTES OPPOSES DU FAISCEAU CENTRAL. UN SYSTEME OPTIQUE CONVERGENT 30 FOCALISE, SUR L'EXTREMITE DU CABLE, UN RAYONNEMENT PROVENANT DES AUBES DE TURBINE 3, LES EXTREMITES DES FAISCEAUX ETANT ORIENTEES DE TELLE MANIERE QUE CHAQUE FAISCEAU RECOIT UN RAYONNEMENT PROVENANT D'UNE ZONE DIFFERENTE A, B, C DE LA LONGUEUR DES AUBES. A L'AUTRE EXTREMITE DU CABLE, CHAQUE FAISCEAU EST CONNECTE A UN DETECTEUR RESPECTIF. UN TEL PYROMETRE EST UTILISABLE NOTAMMENT POUR LE CONTROLE DE TEMPERATURE DES AUBES DANS UN MOTEUR A TURBINE A GAZ.

Alarm device for temperature monitoring

laser thermography

터빈 구성요소의 상태 평가를 위한 비-파괴 방법이 제공된다. 방법은, 터빈 구성요소를 가열하는 광 펄스를 생성하는 레이저를 제공하는 단계를 포함한다. 그런 다음, 가열된 터빈 구성요소의 적외선 이미지가 포착된다. 그런 다음, 터빈 구성요소의 특정 특성에 대한 터빈 구성요소의 분석이 수행될 수 있다. 터빈 구성요소의 비-파괴 상태 평가를 위한 시스템이 또한 제공된다. A non-destructive method for evaluating the condition of a turbine component is provided. The method includes providing a laser that generates a pulse of light that heats a turbine component. An infrared image of the heated turbine component is then captured. An analysis of the turbine component may then be performed for specific characteristics of the turbine component. A system for non-destructive condition assessment of turbine components is also provided.

Fiber optic temperature sensor

A kind of aero engine turbine blades temperature monitoring device

该发明公开了一种用于航空发动机涡轮叶片温度监测装置，涉及温度检测领域，具体说是一种航空发动机涡轮叶片温度监测装置。为了解决航空发动机涡轮叶片温度在线监测中存在的发射率测量困难，燃烧室复杂气体环境干扰等关键科学问题；本发明在温度测量和燃气光谱分析协同工作模式中，两种功能共用一套光路系统，通过燃气光谱分析，选择理想的测温“窗口”，消除燃气吸收造成的辐射衰减，提高测温精度；探头的调焦设计及精确调节控制设计，通过准确的控制扫描伺服与调焦伺服，不断改变光学扫描镜的方位角，并通过调焦来补偿光学准直物镜工作距离的变化，最大程度获得叶片表面不同区域点的辐射量。

Probe head

Die Erfindung betrifft einen Messsondenkopf (1) mit einem Gehäuse (2), das einen Aufnahmeraum (3) und wenigstens einen mit diesem fluidverbundenen Kühlfluidzuführkanal (4) definiert, und zumindest einem in dem Aufnahmeraum (3) aufgenommenen Sensor (5), dadurch gekennzeichnet, dass zumindest ein den Aufnahmeraum (3) umgebender Teilbereich (14) des Gehäuses (2) eine Porosität aufweist, die eine Vielzahl von Kühlfluiddurchtrittsöffnungen (15) definiert.

Radiation-detecting devices and apparatus

A radiation-detecting device which is mounted on a gas-turbine engine to receive radiations from the afterburner combustion-zone, includes a gas-filled electrical discharge tube that is located within a tubular nose of the device and is pulse energized. The ultra-violet component of radiations from the zone and distinctive of the presence of flame in the afterburner, is transmitted to the discharge tube via a sapphire plano-convex lens, the infra-red component being attenuated by a thin gold-film coating on the planar face of the lens, whereby discharge takes place in the tube with each energizing pulse only while the flame is present. The sensitivity of the detecting device to ultra-violet radiation is enhanced by internal reflections from reflective coatings on the inner surface of the tubular nose and the glass envelope of the discharge tube. The count of a counter is advanced stepwise with each pulsing of the discharge tube towards a maximum count of 8 (or 16), and is reset to zero in response to each tube discharge so that the counter overflows only after the tube remains quiescent through more than 8 (or 16) consecutive pulsings. Overflow of the counter signifies positively the flame-out condition and initiates warning and relighting action by a control unit.

Nondestructive testing method and equipment for thermal barrier coating

本发明公开了一种热障涂层无损检测方法，包括：使用线型激光束对样品表面进行快速扫描，形成高密度功率的脉冲热激励并形成热波，以一定频率采集红外热波信号；对采集的红外热波信号处理得到不同时刻的被测区域温度场分布，将获取的不同时刻温度场分布进行叠加，获取样品空间上不同位置的温度场峰值，将不同位置的温度场峰值数据整合得到样品的真实红外成像图；将得到的真实红外成像图去除制定的数据基线，获得去基线后的红外成像数据，对得到的去基线后的红外成像数据进行分析，得到温度场异常区域；对温度场异常区域进行涡流测厚，得到氧化层的厚度。可以实现大面积全景式快速扫描和局部精准测量，能够做到现场实时的高精度无损检测和参数提取。

Asymmetric purge air system for cleaning a lens

A purging air flow system for passing air over a lens (28) to keep it clean and free from particulate contaminants and also for providing a positive flow of air away from the lens (28) has baffles (58A-58D, 96, 104) which cause a flow across the lens (28) that is not symmetrical to avoid a dead air or stagnation zone in the center of the lens (28). The air supply used for such purging is controlled adequately so the flow changes direction and particules are removed from the main flow of purge air by inertial separation prior to the time the air contacts the lens (28). Such air entrained particles might otherwise deposit on the lens (28). A flow control orifice (65) also may provide a secondary flow to carry the particle separated from the main flow out of the flow passageway (39).

Apparatus for observing combustion conditions in a gas turbine engine

A fuel injector for a gas turbine combustor is disclosed which includes a fuel nozzle for issuing fuel into the combustor for combustion, at least one photodetector responsive to flame radiation indicative of an OH chemiluminescence peak, and at least one photodiode responsive to flame radiation indicative of a CH chemiluminescence peak.

Temperature estimation method for high-temperature components, metastable square phase content measurement method, deterioration judgment method

The system and method for the peeling in detecting turbogenerator

本发明涉及用于检测涡轮发动机内的剥落的系统及方法。具体而言，在一个实施例中，一种系统(10)包括多光谱高温测定系统(36)，其构造成用以从涡轮构件(56)接收宽波长带辐射信号(80)、将宽波长带辐射信号(80)分成多个窄波长带辐射信号(94)、基于窄波长带辐射信号(94)来确定涡轮构件(56)的发射率(122)，以及基于发射率(122)来检测涡轮构件(56)表面上的剥落(104)。

Sealing system for optical sensors in gas turbine engines

A sealing system (20) for an optical sensor of a turbine engine that diverts and exhaust seal leakage away from the seal (22, 24) to prevent ingestion of humid air through the seal (22, 24) is disclosed. The sealing system (20) may include inner and outer optical housings (26, 28) with first and second seals (22, 24) positioned there between separating inner and outer optical housings (26, 28) radially. The sealing system (20) may include one or more leakage manifolds (30) positioned between the first and second seals (22, 24) and containing one or more manifold rings (32). The manifold ring (32) may be positioned between and in contact with the first and second seals (22, 24) enabling the first and second seals (22, 24) to form a double seal. The manifold ring (32) may also be configured to capture leakage air that has seeped past the first seal (22) and exhaust that leakage air through one or more exhaust vents (34) in the outer optical housing (28) before leaking through the sealing system (20).

Airplane-mounted external fire detection system

An aircraft-mounted external fire detection system includes optical circuitry and processing circuitry. The optical circuitry is mounted on an aircraft aft of an engine nacelle of the aircraft, and is configured to optically monitor an exterior of the engine nacelle for a hydrocarbon fire by detecting radiation outside of the visible light spectrum. The processing circuitry is communicatively coupled to the optical circuitry and is configured to use the optical circuitry to determine that the fire has been continuously present for more than a threshold duration, and in response, transmit a warning to an operator terminal of the aircraft.

RADIATION PROBE AND METHOD FOR USE THEREOF.

Optical pyrometer sight tube assembly for controlling a gas turbine

Abstract A sight tube assembly, in combination with a sensing instrument, such as an optical pyrometer, for use in continuously monitoring the temperature of the first row of rotating blades in large gas turbines, particularly the type used in industry. Temperature data received by the pyrometer unit is fed to a control circuit, which regulates fuel input to the turbine to control the firing temperature. The key to obtaining reliable blade temperature data in the practice of this invention is the position of the sight tube in the tur-binej which enables the pyrometer to "view" the rotating blades along a direct line of sight that penetrates a hot gas duct, but not the turbine section of the engine.

Laser thermography

FIELD: measurement. SUBSTANCE: invention relates to measurement equipment and relates to non-destructive method of turbine component state estimation. Method includes laser generation of light pulses for heating of the turbine component, capture of infrared images and analysis of characteristics of the turbine component on the obtained images. At that, the method includes laser focusing for pulse illumination of the specified area of the turbine component surface at the first wave length and the first pulse duration, image capturing of the specified area of the component surface, laser focusing for pulsed illumination of the specified zone of the subsurface of the turbine component at the second wave length and the second pulse duration and capture of the second image of the specified zone of the subsurface of the turbine component. EFFECT: technical result consists in acceleration of data analysis when evaluating state of turbine component. 13 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 738 312 C1 (51) МПК G01M 15/14 (2006.01) G01N 21/88 (2006.01) G01N 25/72 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК G01M 15/14 (2020.08); G01N 21/8806 (2020.08); G01N 25/72 (2020.08) (21)(22) Заявка: 2019137967, 03.04.2018 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): СИМЕНС ЭНЕРДЖИ, ИНК. (US) Дата регистрации: 11.12.2020 08.05.2017 US 15/588,853 (45) Опубликовано: 11.12.2020 Бюл. № 35 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 09.12.2019 (86) Заявка PCT: 2 7 3 8 3 1 2 R U (87) Публикация заявки PCT: WO 2018/208387 (15.11.2018) C 1 C 1 US 2018/025819 (03.04.2018) 2 7 3 8 3 1 2 (56) Список документов, цитированных в отчете о поиске: US 5111048 A1, 05.05.1992. US 2015/ 0092814 A1, 02.04.2015. US 2011/0043820 A1, 24.02.2011. US 2002/0027941 A1, 07.03.2002. Приоритет(ы): (30) Конвенционный приоритет: R U 03.04.2018 (72) Автор(ы): БОУДИН, Дастин К. (US), КУЛКАРНИ, ...

Probe device for full-field scanning of engine turbine blade

本发明公开了一种可用于发动机涡轮叶片全场温度扫描的探针装置，包括探针、摆扫转置、旋转装置、伸缩装置、固定底座、固定法兰盘；所述探针包括反射镜、视管、光管、探针外壳、光电转换模块，叶片辐射的光束通过探针传输给光电转换模块；所述伸缩装置包括：滑台底座、螺纹驱动杆、滑台、伸缩控制模块，伸缩控制模块控制滑台的运动从而使探针伸缩运动；所述旋转装置包括：轴承底板、轴承组、外啮合齿轮传动结构、旋转控制模块，所述旋转控制模块控制外啮合齿轮传动结构从而驱动探针旋转；所述摆扫转置包括：反射镜底座、反射镜夹板、反射镜、反射镜销钉、推杆、推杆销钉、摆扫控制模块，所述摆扫控制模块控制推杆的运动从而带动反射镜的摆扫。三个运动控制装置能实现探针的伸缩、旋转以及反射镜的摆扫功能以完成叶片不同叶片高度、叶片不同面以及叶片不同曲率点的扫描最终实现涡轮叶片的全场扫描。

Automated analytics systems and methods

An automated analytics system can include a sensor system that obtains measurement data by monitoring one or more parameters at each of a number of locations on each of a number of replicated components of an object. A computing device receives the measurement data from the sensor system and uses the measurement data to automatically generate a computerized representation of each of the plurality of replicated components. Thereafter, upon receipt of an input query, the computing device generates a synthesized representation of the object that is specifically directed to a parameter of interest indicated in the query. The synthesized representation may be displayed in a visual format that is interpretable by a human to derive information associated with the parameter of interest.

Imaging system for hostile environment optical probe

An optical probe for collecting light from a defined region in a high temperature environment employs a pair of curved surfaces and a reflective surface to couple light from the defined area into an optical fiber while discriminating against light from other regions.

Purge air system for a combustion instrument

ABSTRACT OF THE DISCLOSURE A radiation instrument has a purging air flow system for passing air over the lens to keep it clean and free from particulate contaminants and also for providing a positive flow of air away from the lens . The air supply used for such purging is controlled adequately 80 the flow changes direction and particles are removed from the main flow of purge air by inertial separation prior to the time the air contacts the lens . Such air entrained particles might otherwise deposit on the lens A flow control orifice provides a secondary flow to carry the particles separated from the main flow out of the flow passageway .

Multi-spectral pyrometry imaging system

In one embodiment, a system (10) includes a turbine (18) including multiple components (52, 54, 58, 60, 62, 66, 70, 72) in fluid communication with a working fluid (46) that provides power or thrust. The system (10) also includes an imaging system (36) in optical communication with at least one component (52, 54, 58, 60, 62, 66, 70, 72). The imaging system (36) is configured to receive a broad wavelength band image (74) of the at least one component (52, 54, 58, 60, 62, 66, 70, 72) during operation of the turbine (18), to split the broad wavelength band image (74) into multiple narrow wavelength band images (90, 106, 122, 130, 136, 170, 172, 174, 176), and to output a signal indicative of a two-dimensional intensity map of each narrow wavelength band image (90, 106, 122, 130, 136, 170, 172, 174, 176).

Multi-color pyrometry imaging system and method of operating the same

OPTICAL COMPONENT

Sight tube assembly and sensing instrument for controlling a gas turbine

내용 없음. No content.

Sealing system for optical sensors in gas turbine engines

A sealing system ( 20 ) for an optical sensor of a turbine engine that diverts and exhaust seal leakage away from the seal ( 22, 24 ) to prevent ingestion of humid air through the seal ( 22, 24 ) is disclosed. The sealing system ( 20 ) may include inner and outer optical housings ( 26, 28 ) with first and second seals ( 22, 24 ) positioned there between separating inner and outer optical housings ( 26, 28 ) radially. The sealing system ( 20 ) may include one or more leakage manifolds ( 30 ) positioned between the first and second seals ( 22, 24 ) and containing one or more manifold rings ( 32 ). The manifold ring ( 32 ) may be positioned between and in contact with the first and second seals ( 22, 24 ) enabling the first and second seals ( 22, 24 ) to form a double seal. The manifold ring ( 32 ) may also be configured to capture leakage air that has seeped past the first seal ( 22 ) and exhaust that leakage air through one or more exhaust vents ( 34 ) in the outer optical housing ( 28 ) before leaking through the sealing system ( 20 ).

Be used to generate the multispectral system and method for two-dimension temperature figure

在一个实施例中，一种系统(10)包括成像系统(36)，成像系统(36)配置成从涡轮机(18)的内部接收气体(80)以及可穿过气体(80)观测的表面的图像，将图像分离成指示气体(80)的温度的波长的第一二维强度图和指示表面的温度的波长的第二二维强度图，并输出指示第一和第二二维强度图的信号。