EP1770245B1 - Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz - Google Patents

Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz Download PDF

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Publication number
EP1770245B1
EP1770245B1 EP20050021341 EP05021341A EP1770245B1 EP 1770245 B1 EP1770245 B1 EP 1770245B1 EP 20050021341 EP20050021341 EP 20050021341 EP 05021341 A EP05021341 A EP 05021341A EP 1770245 B1 EP1770245 B1 EP 1770245B1
Authority
EP
European Patent Office
Prior art keywords
hot gas
gas
duct
measuring device
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP20050021341
Other languages
German (de)
English (en)
Other versions
EP1770245A1 (fr
Inventor
Heinz-Jürgen Dr. Groß
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to ES05021341T priority Critical patent/ES2401109T3/es
Priority to EP20050021341 priority patent/EP1770245B1/fr
Publication of EP1770245A1 publication Critical patent/EP1770245A1/fr
Application granted granted Critical
Publication of EP1770245B1 publication Critical patent/EP1770245B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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 running in the component wall and opening into the through-channel, at the second end of which its mouth 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 detection taking place both temporally and locally 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.
  • FIG. 2 shows the device 21 according to the invention for detecting state variables of the flowable in the gas turbine 1 hot gas 11 in a sectional view.
  • 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 lies 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)
  • Measuring Fluid Pressure (AREA)

Claims (4)

  1. Dispositif ( 21 ) de mesure de grandeurs d'état d'un gaz ( 11 ) chaud pouvant passer dans une turbine ( 1 ) à gaz,
    comprenant un canal ( 18 ) pour du gaz chaud pour conduire du gaz ( 11 ) chaud, dans lequel il est prévu au moins une paroi ( 36 ) d'élément sur laquelle passe en partie du gaz ( 11 ) chaud ainsi que
    comprenant un canal ( 37 ) de passage, qui est prévu dans la paroi ( 36 ) de l'élément et qui débouche dans le canal ( 18 ) pour du gaz chaud, canal de passage dans lequel un premier dispositif ( 41 ) de mesure peut être inséré par une entrée ( 39 ) opposée à l'embouchure du canal ( 37 ) de passage, un canal ( 43 ) de communication débouchant dans le canal ( 37 ) de passage,
    caractérisé en ce que
    il est prévu un deuxième dispositif ( 45 ) de mesure sur une seconde extrémité ( 49 ), opposée à l'embouchure ( 51 ), du canal ( 43 ) de communication, dans lequel
    le premier dispositif ( 41 ) de mesure est prévu pour la mesure de la température du gaz ( 11 ) chaud et le deuxième dispositif ( 45 ) de mesure est prévu pour la mesure de la pression du gaz ( 11 ) chaud.
  2. Dispositif ( 21 ) suivant la revendication 1,
    dans lequel le canal ( 43 ) de communication et/ou le canal ( 37 ) de passage sont formés par un tuyau qui est fixé à complémentarité de matière dans la paroi ( 36 ) de l'élément.
  3. Dispositif ( 21 ) suivant la revendication 1 ou 2,
    dans lequel le premier dispositif ( 41 ) de mesure peut être retiré du canal ( 37 ) de passage dans la direction du côté de la paroi ( 36 ) de l'élément éloigné du gaz ( 11 ) chaud.
  4. Dispositif ( 21 ) suivant l'une des revendications 1 à 3,
    dans lequel le canal ( 18 ) pour du gaz chaud fait partie d'une chambre de combustion ( 6 ) de la turbine ( 1 ) à gaz ou fait partie d'un groupe ( 8 ) de turbine de la turbine ( 1 ) à gaz.
EP20050021341 2005-09-29 2005-09-29 Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz Not-in-force EP1770245B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES05021341T ES2401109T3 (es) 2005-09-29 2005-09-29 Dispositivo para la medición de magnitudes de estado de un gas caliente que puede circular en una turbina de gas
EP20050021341 EP1770245B1 (fr) 2005-09-29 2005-09-29 Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20050021341 EP1770245B1 (fr) 2005-09-29 2005-09-29 Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1770245A1 EP1770245A1 (fr) 2007-04-04
EP1770245B1 true EP1770245B1 (fr) 2012-12-12

Family

ID=35976584

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20050021341 Not-in-force EP1770245B1 (fr) 2005-09-29 2005-09-29 Appareil de mesure pour les paramètres d'état d'un gaz chaud dans une turbine à gaz

Country Status (2)

Country Link
EP (1) EP1770245B1 (fr)
ES (1) ES2401109T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3017459B1 (fr) * 2014-02-07 2017-07-21 Snecma Aube instrumentee a tube rapporte dans une rainure
FR3021742B1 (fr) * 2014-05-28 2017-12-29 Snecma Veine instrumentee de turbomachine
US9856743B2 (en) 2014-05-28 2018-01-02 Safran Aircraft Engines Instrumented flow passage of a turbine engine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2394960C (fr) * 2001-08-27 2010-02-16 Mitsubishi Heavy Industries, Ltd. Instrument de mesure de la pression dans une chambre de combustion
US6742394B1 (en) * 2003-01-13 2004-06-01 Power Systems Mfg, Llc Gas turbine combustor hybrid dynamic-static probe
KR100552011B1 (ko) * 2003-01-14 2006-02-20 (주)한울인텍스 가스터빈의 온도감지장치

Also Published As

Publication number Publication date
EP1770245A1 (fr) 2007-04-04
ES2401109T3 (es) 2013-04-17

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