EP1770245A1 - Measuring device for the state conditions of a hot gas flow in a gas turbine engine - Google Patents

Measuring device for the state conditions of a hot gas flow in a gas turbine engine Download PDF

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Publication number
EP1770245A1
EP1770245A1 EP05021341A EP05021341A EP1770245A1 EP 1770245 A1 EP1770245 A1 EP 1770245A1 EP 05021341 A EP05021341 A EP 05021341A EP 05021341 A EP05021341 A EP 05021341A EP 1770245 A1 EP1770245 A1 EP 1770245A1
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EP
European Patent Office
Prior art keywords
hot gas
channel
measuring device
measuring
turbine
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Granted
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EP05021341A
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German (de)
French (fr)
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EP1770245B1 (en
Inventor
Heinz-Jürgen Dr. Groß
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Siemens AG
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Siemens AG
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Priority to EP20050021341 priority Critical patent/EP1770245B1/en
Priority to ES05021341T priority patent/ES2401109T3/en
Publication of EP1770245A1 publication Critical patent/EP1770245A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • F01D17/085—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure to temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure

Definitions

  • the invention relates to a device for measuring state variables of a hot gas that can be flowed in a gas turbine, having a hot gas channel for guiding the hot gas, in which at least one partially surrounded by the hot gas component wall is provided as well as with a provided in the component wall and opening into the hot gas channel feedthrough channel for insertion a measuring device.
  • a temperature measuring device for a gas turbine known.
  • a temperature sensor is provided at the tip of the lance-type temperature measuring device and surrounded by a housing tube protecting the sensor.
  • the housing tube has a threaded portion at its second end opposite the tip for attaching the temperature measuring device to a turbine.
  • the tip of the temperature measuring device is inserted through a corresponding channel and screwed to the holder. Subsequently, the exchangeable temperature measuring device is connected to a control unit.
  • a measuring device with a measuring sensor for measuring the pressure of a combustion gas flowing in a combustion chamber of a gas turbine known.
  • the measuring device also has a pressure line, which fluidly connects the combustion chamber with the pressure sensor.
  • the pressure of the combustion gas occurring in the combustion chamber is forwarded via the pressure line to the spaced pressure sensor and can be detected by the latter in a cooler area easily and reliably. Due to the pressure line can occur in this during operation resonant vibrations, which are compensated by a damping tube.
  • the damping tube opens into the pressure line and is helically wound around the pressure line.
  • the disadvantage is that for measuring each state variable in each case a separate device and support for the measuring devices is necessary.
  • a correction calculation for the respective size as a function of the measuring location may be required.
  • the object of the present invention is to improve the detection of state variables of a hot gas that can be flowed in a gas turbine.
  • the invention proposes that the generic device has a communication channel extending in the component wall and opening into the through-channel, at the second end of which its opposite end is provided a second measuring device.
  • the invention is based on the recognition that at least one to be detected Great, for example, the pressure of the hot gas, propagates approximately lossless from the combustion chamber via the feed channel into the communication channel, so that also in the feed channel, a second state variable of the hot gas is detected locally bounded.
  • the invention in addition to the combined detection of a plurality of state variables in one measuring location with respect to the hot gas channel, the invention also makes possible a particularly simple further processing of the detected values in a closed-loop control or monitoring, since the detected values are particularly due to the temporally and spatially coincident detection provide exact state variables of the hot gas.
  • the measuring sensor or the measuring sensor of the first measuring device inserted into the feedthrough channel is arranged in the operating position in the mouth region or slightly outside the feedthrough channel in the hot gas channel, a particularly efficient detection of the state variables can be achieved respectively. An improved usability of the state variables determined thereby is thus also achieved. Accordingly, the operation of a gas turbine equipped therewith can be optimized.
  • the cost of manufacturing the channels and mounting the measuring devices is reduced due to a reduced number of structural components.
  • the first measuring device for measuring the temperature of the hot gas and the second measuring device for measuring the pressure of the hot gas is provided.
  • a combined pressure and temperature measurement of the hot gas flowing around a turbine blade for example, can be carried out under operating conditions without a correction calculation having to be carried out for one of the two state variables for adjusting the state variables previously measured at different locations by the control unit of the gas turbine.
  • the communication channel and / or the passage channel are formed by a extending through the component tube, which is firmly bonded in the component wall, preferably by a solder joint.
  • the hitherto also usual erosion and soldering the temperature measuring device, such as a thermocouple is no longer necessary.
  • the first measuring device can be removed from the feed channel in the direction of the side of the component wall facing away from the hot gas. This allows the replacement of a defective first measuring device, without access to the hot gas channel of the gas turbine is required. This reduces the processing time in the case of maintenance and thus increases the availability of the gas turbine equipped with it.
  • the hot gas duct is part of a combustion chamber of the gas turbine or part of a turbine unit of the gas turbine.
  • the proposed invention can provide a particularly simple device for measuring the pressure and the temperature of a hot gas flowing through the gas turbine.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • the sectional view shows a hollow, designed as a guide blade 12 turbine blade 23 of the gas turbine 1.
  • the turbine blade 23 has a fixed to a vane carrier not shown vane root 25 and a fixed in a rotor 3 immediately surrounding mounting ring guide vane head 27.
  • the turbine blade 23 further comprises a respective platform 29, 31, both of which serve as a hot gas channel boundary. Between the platforms 29, 31, seen in the flow direction of the hot gas 11 extends aerodynamically optimized airfoil 33rd
  • the first end 35 opens open in the illustrated embodiment in the platform 31 and is preferably soldered.
  • Other attachment variants are conceivable.
  • the pipe system comprises a feedthrough channel 37 which, starting at the foot end, subsequently extends through the airfoil profile 33 of the turbine blade 23 and ends in an arc 39 at the head end.
  • the passage channel 37 opens open in a component wall 36, for example in the head-side platform 31, where the hot gas 11 can flow along.
  • a first lance-like measuring device 41 for example a temperature sensor inserted.
  • the measuring device 41 is inserted so deeply into the feedthrough channel 37 that a measuring tip 53 of the measuring device 41 is arranged in the mouth region 47 of the feedthrough channel 37 or protrudes slightly into the hot gas channel 18.
  • the measuring device 41 could detect, for example, the chemical composition of the hot gas 11 or the emission concentration with suitable sensors.
  • a second channel the communication channel 43 which, on the one hand, opens into the feed-through channel and, on the other hand, has a second measuring device 45, in particular a measuring sensor for pressure detection.
  • the airfoil profile 33 of the turbine blade 23 is flowed around by the hot gas 11 generated in the combustion chamber 6.
  • the hot gas 11 flows in the turbine unit 8 along the component wall 36, which is also formed by platforms 29, 31.
  • the pressure of the hot gas 11 occurring in the hot gas channel 18 propagates through the mouth 47 of the passage channel 37 in this. Accordingly, the identical pressure of the hot gas 11 prevails both in the feedthrough channel 37 and in the communication channel 43 connected therewith in terms of flow, since a sufficiently large distance is provided between the inserted first measuring device 41 and the channel wall of the feedthrough channel. As a result, the pressure of the hot gas 11 from the second measuring device 45 can be detected at the end 49 of the communication channel 47, which is opposite its mouth 51 in the through-channel 37, in a cooler region.
  • the inserted first measuring device 41 detects at the measuring tip 53, the temperature of the hot gas 11. Since the pressure of the hot gas 11 from the mouth 47 of the through-channel 37 to the end 49 of the communication channel 43 occurs unchanged, an identical measuring location is given for both detected state variables of the hot gas 11, namely the measuring tip 53.

Abstract

An assembly (21) measures a gas (11) parameter in a gas passage (18) formed by a wall (36) in a gas turbine engine (1). The engine has a guide vane head with an aperture to a bleed passage through which a lance (41) is inserted, the tip (53) slightly protruding into the gas inlet (35). The duct (37) has a side-branch (43) to a sensor (45).

Description

Die Erfindung betrifft eine Vorrichtung zur Messung von Zustandsgrößen eines in einer Gasturbine strömbaren Heißgases, mit einem Heißgaskanal zum Führen des Heißgases, in dem zumindest eine teilweise vom Heißgas umströmte Bauteilwand vorgesehen ist sowie mit einem in der Bauteilwand vorgesehenen und in den Heißgaskanal mündenden Durchführungskanal zum Einführen einer Messvorrichtung.The invention relates to a device for measuring state variables of a hot gas that can be flowed in a gas turbine, having a hot gas channel for guiding the hot gas, in which at least one partially surrounded by the hot gas component wall is provided as well as with a provided in the component wall and opening into the hot gas channel feedthrough channel for insertion a measuring device.

Aus der KR 2004065502 eine Temperaturmesseinrichtung für eine Gasturbine bekannt. Ein Temperatursensor ist an der Spitze der lanzenartigen Temperaturmesseinrichtung vorgesehen und von einem den Sensor schützenden Gehäuserohr umgeben. Das Gehäuserohr hat an seinem zweiten, der Spitze gegenüberliegendem Ende einen Verschraubungsabschnitt zum Befestigen der Temperaturmesseinrichtung an einer Turbine. Um die Temperatur des in der Turbine strömenden Heißgases zu messen, wird die Spitze der Temperaturmesseinrichtung durch einen dazu korrespondierenden Kanal eingeschoben und mit der Halterung verschraubt. Anschließend wird die austauschbare Temperaturmesseinrichtung mit einer Reglereinheit verbunden.From the KR 2004065502 a temperature measuring device for a gas turbine known. A temperature sensor is provided at the tip of the lance-type temperature measuring device and surrounded by a housing tube protecting the sensor. The housing tube has a threaded portion at its second end opposite the tip for attaching the temperature measuring device to a turbine. In order to measure the temperature of the hot gas flowing in the turbine, the tip of the temperature measuring device is inserted through a corresponding channel and screwed to the holder. Subsequently, the exchangeable temperature measuring device is connected to a control unit.

Zudem ist aus der EP 1 288 642 A2 eine Messeinrichtung mit einem Messsensor zur Messung des Druckes eines in einer Brennkammer einer Gasturbine strömenden Verbrennungsgases bekannt. Die Messeinrichtung weist ferner eine Druckleitung auf, die die Brennkammer mit dem Drucksensor strömungstechnisch verbindet. Der in der Brennkammer auftretende Druck des Verbrennungsgases wird über die Druckleitung zu dem beabstandeten Drucksensor weitergeleitet und kann von diesem in einem kühleren Bereich einfach und zuverlässig erfasst werden. Aufgrund der Druckleitung können in dieser beim Betrieb Resonanzschwingungen auftreten, welche durch ein Dämpfungsrohr kompensiert werden. Das Dämpfungsrohr mündet in die Druckleitung und ist schraubenförmig um die Druckleitung gewunden.Moreover, from the EP 1 288 642 A2 a measuring device with a measuring sensor for measuring the pressure of a combustion gas flowing in a combustion chamber of a gas turbine known. The measuring device also has a pressure line, which fluidly connects the combustion chamber with the pressure sensor. The pressure of the combustion gas occurring in the combustion chamber is forwarded via the pressure line to the spaced pressure sensor and can be detected by the latter in a cooler area easily and reliably. Due to the pressure line can occur in this during operation resonant vibrations, which are compensated by a damping tube. The damping tube opens into the pressure line and is helically wound around the pressure line.

Nachteilig ist, dass zur Messung jeder Zustandsgröße jeweils eine separate Vorrichtung und Halterung für die Messeinrichtungen notwendig ist. Außerdem kann zur weiteren Verarbeitung der erfassten Messgrößen, beispielsweise in einer Regelung oder Überwachung, eine Korrekturrechnung für die jeweilige Größe in Abhängigkeit des Messortes erforderlich sein.The disadvantage is that for measuring each state variable in each case a separate device and support for the measuring devices is necessary. In addition, for further processing of the detected measured variables, for example in a control or monitoring, a correction calculation for the respective size as a function of the measuring location may be required.

Aufgabe der vorliegenden Erfindung ist die Verbesserung der Erfassung von Zustandsgrößen eines in einer Gasturbine strömbaren Heißgases.The object of the present invention is to improve the detection of state variables of a hot gas that can be flowed in a gas turbine.

Diese Aufgabe wird durch eine Vorrichtung gemäß den Merkmalen des Patentanspruchs 1 gelöst. Die Erfindung schlägt vor, dass die gattungsgemäße Vorrichtung einen in der Bauteilwand verlaufenden und in den Durchgangskanal mündenden Kommunikationskanal aufweist, an dessen zweitem seiner Mündung gegenüberliegendem Ende eine zweite Messeinrichtung vorgesehen ist. Die Erfindung geht von der Erkenntnis aus, dass mindestens eine zu erfassende Große, beispielsweise der Druck des Heißgases, sich annähernd verlustfrei aus der Brennkammer über den Durchführungskanal bis in den Kommunikationskanal fortpflanzt, so dass außerdem im Durchführungskanal eine zweite Zustandsgröße des Heißgases ortsgebunden erfassbar ist. Somit ist durch die Erfindung neben einer kombinierten Erfassung mehrerer Zustandsgrößen in einem Messort - bezogen auf den Heißgaskanal - auch eine besonders einfache weitere Verarbeitung der erfassten Werte in einer Regelung oder Überwachung möglich, da die erfassten Werte aufgrund der sowohl zeitlich als auch örtlich übereinstimmenden Erfassung besonders exakte Zustandgrößen des Heißgases liefern.This object is achieved by a device according to the features of patent claim 1. The invention proposes that the generic device has a communication channel extending in the component wall and opening into the through-channel, at the second end of which its opposite end is provided a second measuring device. The invention is based on the recognition that at least one to be detected Great, for example, the pressure of the hot gas, propagates approximately lossless from the combustion chamber via the feed channel into the communication channel, so that also in the feed channel, a second state variable of the hot gas is detected locally bounded. Thus, in addition to the combined detection of a plurality of state variables in one measuring location with respect to the hot gas channel, the invention also makes possible a particularly simple further processing of the detected values in a closed-loop control or monitoring, since the detected values are particularly due to the temporally and spatially coincident detection provide exact state variables of the hot gas.

Insbesondere, wenn der Messfühler bzw. der Messsensor der in den Durchführungskanal eingeschobenen ersten Messeinrichtung in der Betriebslage im Mündungsbereich oder geringfügig außerhalb des Durchführungskanals im Heißgaskanal angeordnet ist, kann eine besonders effiziente Erfassung der Zustandsgrößen erfolgen. Eine verbessere Verwertbarkeit der dadurch ermittelten Zustandsgrößen wird somit auch erreicht. Dementsprechend kann der Betrieb einer damit ausgerüsteten Gasturbine optimiert werden.In particular, if the measuring sensor or the measuring sensor of the first measuring device inserted into the feedthrough channel is arranged in the operating position in the mouth region or slightly outside the feedthrough channel in the hot gas channel, a particularly efficient detection of the state variables can be achieved respectively. An improved usability of the state variables determined thereby is thus also achieved. Accordingly, the operation of a gas turbine equipped therewith can be optimized.

Außerdem sind die Kosten für die Herstellung der Kanäle und die Anbringung der Messeinrichtungen aufgrund einer reduzierten Anzahl an strukturellen Bauelementen geringer.In addition, the cost of manufacturing the channels and mounting the measuring devices is reduced due to a reduced number of structural components.

Vorteilhafte Ausgestaltungen werden in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

Besonders vorteilhaft ist die erste Messeinrichtung zur Messung der Temperatur des Heißgases und die zweite Messeinrichtung zur Messung des Druckes des Heißgases vorgesehen. Hierdurch kann eine kombinierte Druck- und Temperaturmessung des beispielsweise eine Turbinenschaufel umströmenden Heißgases unter Betriebsbedingungen erfolgen, ohne dass eine Korrekturrechung für eine der beiden Zustandsgrößen zum Anpassen der bisher an unterschiedlichen Orten gemessenen Zustandsgrößen von der Reglereinheit der Gasturbine durchgeführt werden muss.Particularly advantageously, the first measuring device for measuring the temperature of the hot gas and the second measuring device for measuring the pressure of the hot gas is provided. As a result, a combined pressure and temperature measurement of the hot gas flowing around a turbine blade, for example, can be carried out under operating conditions without a correction calculation having to be carried out for one of the two state variables for adjusting the state variables previously measured at different locations by the control unit of the gas turbine.

In einer vorteilhaften Weiterbildung werden der Kommunikationskanal und/oder der Durchführungskanal von einem sich durch das Bauteil erstreckenden Rohr gebildet, welches in der Bauteilwand stoffschlüssig, vorzugsweise durch eine Lötverbindung, befestigt ist. Das bisher auch übliche Erodieren und Einlöten der Temperaturmesseinrichtung, beispielsweise eines Thermoelementes ist nicht mehr nötig.In an advantageous development of the communication channel and / or the passage channel are formed by a extending through the component tube, which is firmly bonded in the component wall, preferably by a solder joint. The hitherto also usual erosion and soldering the temperature measuring device, such as a thermocouple is no longer necessary.

Zweckmäßigerweise ist die erste Messeinrichtung dem Durchführungskanal in Richtung der dem Heißgas abgewandten Seite der Bauteilwand entnehmbar. Dies ermöglicht das Austauschen einer defekten ersten Messeinrichtung, ohne dass ein Zugang zu dem Heißgaskanal der Gasturbine erforderlich ist. Dies reduziert im Wartungsfall die Bearbeitungsdauer und erhöht somit die Verfügbarkeit der damit ausgerüsteten Gasturbine.Expediently, the first measuring device can be removed from the feed channel in the direction of the side of the component wall facing away from the hot gas. This allows the replacement of a defective first measuring device, without access to the hot gas channel of the gas turbine is required. This reduces the processing time in the case of maintenance and thus increases the availability of the gas turbine equipped with it.

Vorzugsweise ist der Heißgaskanal Teil einer Brennkammer der Gasturbine oder Teil einer Turbineneinheit der Gasturbine. Insbesondere, wenn die Messungen im Bereich von Turbinenschaufeln durchgeführt werden sollen, kann mit der vorgeschlagenen Erfindung eine besonders einfache Vorrichtung zur Messung des Druckes und der Temperatur eines die Gasturbine durchströmenden Heißgases angegeben werden.Preferably, the hot gas duct is part of a combustion chamber of the gas turbine or part of a turbine unit of the gas turbine. In particular, if the measurements are to be carried out in the region of turbine blades, the proposed invention can provide a particularly simple device for measuring the pressure and the temperature of a hot gas flowing through the gas turbine.

Eine beispielhafte Ausführungsvariante der Erfindung wird anhand der Zeichnung erläutert. Es zeigen:

FIG 1
einen Längsteilschnitt durch eine Gasturbine und
FIG 2
die erfindungsgemäße Vorrichtung zum Messen von Zustandsgrößen eines in einer Gasturbine strömbaren Heißgases in einer Schnittdarstellung.
An exemplary embodiment of the invention will be explained with reference to the drawing. Show it:
FIG. 1
a longitudinal section through a gas turbine and
FIG. 2
the inventive device for measuring state variables of a hot gas flowing in a gas turbine in a sectional view.

FIG 1 zeigt eine Gasturbine 1 in einem Längsteilschnitt. Sie weist im Inneren einen um eine Rotationsachse 2 drehgelagerten Rotor 3 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine torusartige Ringbrennkammer 6 mit mehreren rotationssymmetrisch zueinander angeordneten Brennern 7, eine Turbineneinheit 8 und ein Abgasgehäuse 9. Die Ringbrennkammer 6 bildet einen Verbrennungsraum 17, der mit einem ringförmigen Heißgaskanal 18 kommuniziert. Dort bilden vier hintereinander geschaltete Turbinenstufen 10 die Turbineneinheit 8. Jede Turbinenstufe 10 ist aus zwei Schaufelringen gebildet. In Strömungsrichtung eines in der Ringbrennkammer 6 erzeugten Heißgases 11 gesehen, folgt im Heißgaskanal 18 jeweils einer Leitschaufelreihe 13 eine aus Laufschaufeln 15 gebildete Reihe 14. Die Leitschaufeln 12 sind am Stator befestigt, wohingegen die Laufschaufeln 15 einer Reihe 14 mittels einer Turbinenscheibe am Rotor 3 angebracht sind. An dem Rotor 3 ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt) angekoppelt.1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9. The annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18. There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings. As seen in the flow direction of a hot gas 11 produced in the annular combustion chamber 6, in the hot gas channel 18 in each case one row of blades 13 followed by a number of rows of blades 14. The vanes 12 are attached to the stator, whereas the blades 15 a row 14 mounted by means of a turbine disk on the rotor 3 are. On the rotor 3, a generator or a working machine (not shown) is coupled.

FIG 2 zeigt die erfindungsgemäße Vorrichtung 21 zum Erfassen von Zustandsgrößen des in der Gasturbine 1 strömbaren Heißgases 11 in einer Schnittdarstellung. Die Schnittdarstellung zeigt eine hohle, als Leitschaufel 12 ausgebildete Turbinenschaufel 23 der Gasturbine 1. Die Turbinenschaufel 23 weist einen an einen nicht dargestellten Leitschaufelträger festgelegten Schaufelfuß 25 und einen in einem den Rotor 3 unmittelbar umgreifenden Befestigungsring festlegbaren Leitschaufelkopf 27 auf. Sowohl kopfseitig als auch fußseitig umfasst die Turbinenschaufel 23 ferner jeweils eine Plattform 29, 31, die beide als Heißgaskanalbegrenzung dienen. Zwischen den Plattformen 29, 31 erstreckt sich ein in Strömungsrichtung des Heißgases 11 gesehen aerodynamisch optimiertes Tragflächenprofil 33.2 shows the device 21 according to the invention for detecting state variables of the hot gas 11 that can be flowed in the gas turbine 1 in a sectional illustration. The sectional view shows a hollow, designed as a guide blade 12 turbine blade 23 of the gas turbine 1. The turbine blade 23 has a fixed to a vane carrier not shown vane root 25 and a fixed in a rotor 3 immediately surrounding mounting ring guide vane head 27. On both the head and the foot side, the turbine blade 23 further comprises a respective platform 29, 31, both of which serve as a hot gas channel boundary. Between the platforms 29, 31, seen in the flow direction of the hot gas 11 extends aerodynamically optimized airfoil 33rd

Im Inneren der hohlen Turbinenschaufel 23 ist ein Rohrsystem eingebracht und befestigt, dessen erstes Ende 35 im gezeigten Ausführungsbeispiel in der Plattform 31 offen mündet und vorzugsweise eingelötet ist. Andere Befestigungsvarianten sind denkbar.In the interior of the hollow turbine blade 23, a pipe system is introduced and fastened, the first end 35 opens open in the illustrated embodiment in the platform 31 and is preferably soldered. Other attachment variants are conceivable.

Das Rohrsystem umfasst einen Durchführungskanal 37, der fußseitig beginnend sich anschließend durch das Tragflächenprofil 33 der Turbinenschaufel 23 erstreckt und kopfseitig in einem Bogen 39 endet. Der Durchführungskanal 37 mündet offen in einer Bauteilwand 36, beispielsweise in der kopfseitigen Plattform 31, an der das Heißgas 11 entlang strömen kann. In den Durchführungskanal 37 ist am dem Heißgas 11 abgewandten Ende, also an der fußseitigen Einführung 39, eine erste lanzenartige Messeinrichtung 41, beispielsweise ein Temperatursensor einschiebbar. Dabei wird die Messeinrichtung 41 derart tief in den Durchführungskanal 37 eingeschoben, dass eine Messspitze 53 der Messeinrichtung 41 im Mündungsbereich 47 des Durchführungskanals 37 angeordnet ist oder geringfügig in den Heißgaskanal 18 hinein ragt. Anstelle der Temperatur könnte die Messeinrichtung 41 beispielsweise auch die chemische Zusammensetzung des Heißgases 11 oder die Emissionskonzentration mit geeigneten Sensoren erfassen.The pipe system comprises a feedthrough channel 37 which, starting at the foot end, subsequently extends through the airfoil profile 33 of the turbine blade 23 and ends in an arc 39 at the head end. The passage channel 37 opens open in a component wall 36, for example in the head-side platform 31, where the hot gas 11 can flow along. In the passage channel 37 is at the end facing away from the hot gas 11, ie at the foot-side introduction 39, a first lance-like measuring device 41, for example a temperature sensor inserted. In this case, the measuring device 41 is inserted so deeply into the feedthrough channel 37 that a measuring tip 53 of the measuring device 41 is arranged in the mouth region 47 of the feedthrough channel 37 or protrudes slightly into the hot gas channel 18. Instead of the temperature, the measuring device 41 could detect, for example, the chemical composition of the hot gas 11 or the emission concentration with suitable sensors.

Im fußseitigen Bereich der Turbinenschaufel 23 ist ein zweiter Kanal, der Kommunikationskanal 43, vorgesehen, der einerseits in den Durchführungskanal mündet und der andererseits eine zweite Messeinrichtung 45, insbesondere einen Messsensor zur Druckerfassung aufweist.In the foot-side region of the turbine blade 23, a second channel, the communication channel 43, is provided which, on the one hand, opens into the feed-through channel and, on the other hand, has a second measuring device 45, in particular a measuring sensor for pressure detection.

Beim Betrieb der Gasturbine 1 wird das Tragflächenprofil 33 der Turbinenschaufel 23 von dem in der Brennkammer 6 erzeugten Heißgas 11 umströmt. Das Heißgas 11 strömt in der Turbineneinheit 8 entlang der auch von Plattformen 29, 31 gebildeten Bauteilwand 36.During operation of the gas turbine 1, the airfoil profile 33 of the turbine blade 23 is flowed around by the hot gas 11 generated in the combustion chamber 6. The hot gas 11 flows in the turbine unit 8 along the component wall 36, which is also formed by platforms 29, 31.

Der im Heißgaskanal 18 auftretende Druck des Heißgases 11 pflanzt sich über die Mündung 47 des Durchführungskanals 37 in diesem fort. Demnach herrscht sowohl im Durchführungskanal 37 als auch im damit strömungstechnisch verbundenen Kommunikationskanal 43 der identische Druck des Heißgases 11, da zwischen eingeschobener erster Messeinrichtung 41 und der Kanalwand des Durchführungskanals ein dafür genügend großer Abstand vorgesehen ist. Dadurch kann am Ende 49 des Kommunikationskanals 47, welches seiner Mündung 51 im Durchgangskanal 37 gegenüberliegt, in einem kühleren Bereich der Druck des Heißgases 11 von der zweiten Messeinrichtung 45 erfasst werden.The pressure of the hot gas 11 occurring in the hot gas channel 18 propagates through the mouth 47 of the passage channel 37 in this. Accordingly, the identical pressure of the hot gas 11 prevails both in the feedthrough channel 37 and in the communication channel 43 connected therewith in terms of flow, since a sufficiently large distance is provided between the inserted first measuring device 41 and the channel wall of the feedthrough channel. As a result, the pressure of the hot gas 11 from the second measuring device 45 can be detected at the end 49 of the communication channel 47, which is opposite its mouth 51 in the through-channel 37, in a cooler region.

Zugleich ist es durch die eingeschobene erste Messeinrichtung 41 möglich, an dessen Messspitze 53 die Temperatur des Heißgases 11 zu erfassen. Da der Druck des Heißgases 11 von der Mündung 47 des Durchgangskanals 37 bis zum Ende 49 des Kommunikationskanals 43 unverändert auftritt, ist für beide erfassten Zustandsgrößen des Heißgases 11 ein identischer Messort gegeben, nämlich die Messspitze 53.At the same time, it is possible by the inserted first measuring device 41 to detect at the measuring tip 53, the temperature of the hot gas 11. Since the pressure of the hot gas 11 from the mouth 47 of the through-channel 37 to the end 49 of the communication channel 43 occurs unchanged, an identical measuring location is given for both detected state variables of the hot gas 11, namely the measuring tip 53.

Claims (5)

Vorrichtung (21) zur Messung von Zustandsgrößen eines in einer Gasturbine (1) strömbaren Heißgases (11), mit einem Heißgaskanal (18) zum Führen des Heißgases (11), in dem zumindest eine teilweise vom Heißgas (11) umströmte Bauteilwand (36) vorgesehen ist sowie mit einem in der Bauteilwand (36) vorgesehenen und in den Heißgaskanal (18) mündenden Durchführungskanal (37), in den eine erste Messeinrichtung (41) durch eine der Mündung gegenüberliegende Einführung (39) des Durchführkanals (37) einschiebbar ist,
dadurch gekennzeichnet, dass
ein Kommunikationskanal (43) in den Durchgangskanal (37) mündet, an dessen zweitem seiner Mündung (51) gegenüberliegenden Ende (49) eine zweite Messeinrichtung (45) vorgesehen ist.Device (21) for measuring state variables of a hot gas (11) which can be flowed in a gas turbine (1), having a hot gas channel (18) for guiding the hot gas (11), in which at least one component wall (36) surrounded by the hot gas (11) is flowed around. is provided and with a in the component wall (36) provided and in the hot gas channel (18) opening out feed channel (37) into which a first measuring device (41) through an opening opposite the introduction (39) of the feedthrough channel (37) can be inserted,
characterized in that
a communication channel (43) opens into the through-channel (37), at whose second end (49) opposite its mouth (51) a second measuring device (45) is provided. Vorrichtung (21) nach Anspruch 1,
bei der die erste Messeinrichtung (41) zur Messung der Temperatur des Heißgases (11) und die zweite Messeinrichtung (45) zur Messung des Druckes des Heißgases (11) vorgesehen ist.Device (21) according to claim 1,
in which the first measuring device (41) for measuring the temperature of the hot gas (11) and the second measuring device (45) for measuring the pressure of the hot gas (11) is provided. Vorrichtung (21) nach Anspruch 1 oder 2,
bei der der Kommunikationskanal (43) und/oder der Durchführungskanal (37) von einem Rohr gebildet werden, welches in der Bauteilwand (36) stoffschlüssig befestigt ist.Device (21) according to claim 1 or 2,
in which the communication channel (43) and / or the feedthrough channel (37) are formed by a tube which is firmly bonded in the component wall (36). Vorrichtung (21) nach einem der Ansprüche 1 bis 3,
bei der die erste Messeinrichtung (41) dem Durchführungskanal (37) in Richtung der dem Heißgas (11) abgewandten Seite der Bauteilwand (36) entnehmbar ist.Device (21) according to one of claims 1 to 3,
in which the first measuring device (41) can be removed from the feed channel (37) in the direction of the side of the component wall (36) facing away from the hot gas (11). Vorrichtung (21) nach einem der Ansprüche 1 bis 4,
bei der der Heißgaskanal (18) Teil einer Brennkammer (6) der Gasturbine (1) oder Teil einer Turbineneinheit (8) der Gasturbine (1) ist.Device (21) according to one of claims 1 to 4,
in which the hot gas duct (18) is part of a combustion chamber (6) of the gas turbine (1) or part of a turbine unit (8) of the gas turbine (1).
EP20050021341 2005-09-29 2005-09-29 Measuring device for the state conditions of a hot gas flow in a gas turbine engine Not-in-force EP1770245B1 (en)

Priority Applications (2)

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EP20050021341 EP1770245B1 (en) 2005-09-29 2005-09-29 Measuring device for the state conditions of a hot gas flow in a gas turbine engine
ES05021341T ES2401109T3 (en) 2005-09-29 2005-09-29 Device for measuring status quantities of a hot gas that can circulate in a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20050021341 EP1770245B1 (en) 2005-09-29 2005-09-29 Measuring device for the state conditions of a hot gas flow in a gas turbine engine

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FR3017459A1 (en) * 2014-02-07 2015-08-14 Snecma AUBE INSTRUMENTEE A TUBE REPORTED IN A GROOVE
FR3021742A1 (en) * 2014-05-28 2015-12-04 Snecma INSTRUMED VEIN OF TURBOMACHINE
US9856743B2 (en) 2014-05-28 2018-01-02 Safran Aircraft Engines Instrumented flow passage of a turbine engine

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EP1288642A2 (en) * 2001-08-27 2003-03-05 Mitsubishi Heavy Industries, Ltd. Measuring pressure in a combustor ( gas turbine ) : Damping tube without moisture condensation and bundled tubes
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Publication number Priority date Publication date Assignee Title
FR3017459A1 (en) * 2014-02-07 2015-08-14 Snecma AUBE INSTRUMENTEE A TUBE REPORTED IN A GROOVE
US9777590B2 (en) 2014-02-07 2017-10-03 Snecma Instrumented vane
FR3021742A1 (en) * 2014-05-28 2015-12-04 Snecma INSTRUMED VEIN OF TURBOMACHINE
US9856743B2 (en) 2014-05-28 2018-01-02 Safran Aircraft Engines Instrumented flow passage of a turbine engine

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ES2401109T3 (en) 2013-04-17

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