WO2012175302A1 - Turbine à gaz dotée d'un pyromètre - Google Patents

Turbine à gaz dotée d'un pyromètre Download PDF

Info

Publication number
WO2012175302A1
WO2012175302A1 PCT/EP2012/060209 EP2012060209W WO2012175302A1 WO 2012175302 A1 WO2012175302 A1 WO 2012175302A1 EP 2012060209 W EP2012060209 W EP 2012060209W WO 2012175302 A1 WO2012175302 A1 WO 2012175302A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
optical waveguide
radiation
collimator
blade
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.)
Ceased
Application number
PCT/EP2012/060209
Other languages
German (de)
English (en)
Inventor
Thomas Bosselmann
Michael Willsch
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP12726080.0A priority Critical patent/EP2723994A1/fr
Priority to US14/126,437 priority patent/US20140133994A1/en
Priority to JP2014516256A priority patent/JP2014522964A/ja
Publication of WO2012175302A1 publication Critical patent/WO2012175302A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/0088—Radiation pyrometry, e.g. infrared or optical thermometry in turbines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/02—Constructional details
    • G01J5/08—Optical arrangements
    • G01J5/0818—Waveguides
    • G01J5/0821—Optical fibres
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Definitions

  • Gas turbine pyrometer The invention relates to a gas turbine with at least one stationary guide blade and at least one rotor blade in operation ro ⁇ -mountable.
  • the efficiency of modern gas turbines is constantly being worked on. An increased efficiency can always be achieved by an increased operating temperature.
  • the operating temperature is constantly approaching the limits of the temperature resistance of the materials used in the blades.
  • the temperature of individual components of a gas turbine is monitored.
  • pyrometers are used, for example, which record the thermal radiation of individual components, conduct it to a detector and evaluate it, thereby determining the temperature of the component.
  • a plurality of temperature measurement points, and temperature measuring equipment is used.
  • the stationary vanes have greater inhomogeneities in temperature distribution than the rotating vanes due to their fixed position relative to the burners.
  • the temperature distribution in the guide vanes is therefore of great interest. So far, the temperature of the vanes is measured at points with a limited number of stationary thermocouples.
  • the gas turbine according to the invention comprises at least one ste ⁇ immediate vane and at least one rotatable rotor blade during operation. Furthermore, at least one embedded in a first blade optical waveguide is present, which is aligned so that thermal radiation of a first Leit ⁇ scoop is received by the optical waveguide.
  • the gas turbine according to the invention further includes an off ⁇ values facility for evaluation of thermal radiation.
  • the evaluation device is configured to determine the temperature of at least the first guide vane, wherein the temperature can be determined along a path from which the thermal radiation is recorded during the rotation of the first moving blade and thus of the optical waveguide.
  • the region of the vane whose thermal radiation is absorbed depends on the optical waveguide and on the distance of the optical waveguide end from the vane. In other words, the pyrometer rotates through the
  • Optical waveguide is represented, in the invention with a blade with, and is on a vane court ⁇ tet.
  • the first blade comprises a photodetector for converting the heat radiation into electrical signals.
  • the photodetector is expediently coupled to the optical waveguide in order to be able to absorb the thermal radiation which comes from the first vane after passing through the optical waveguide.
  • the photodetector may in this case be supplied for example by a wire ⁇ energy transfer.
  • the Photodetector be powered by a battery. Advantage ⁇ way is thus largely realized the pyrometer in the blade itself. The determined data can then be recorded or forwarded by telemetry or by a co-rotating data recorder.
  • the optical waveguide is guided into the shaft of the first blade and ends there.
  • Parts of the gas turbine are delivered. It can be easily recorded and processed there. It is advantageous if the end of the optical waveguide in the Wel ⁇ le is provided with a collimator. In this way, according to an advantageous embodiment of the invention, the exiting heat radiation can be emitted in an axial parallel beam. This makes it possible to absorb the radiation as far as possible without attenuation after passing through a short air gap.
  • the radiation coming from the collimator is picked up by a recording device, wherein the receiving region of the recording device is designed over such a large area that essentially all radiation coming from the collimator can be received.
  • the relatively large surface area configuration of the recording ⁇ device makes it possible to take the heat radiation lossless and further processing. This preserves the accuracy of the measurement.
  • the receiving device is an optical waveguide, in particular an optical waveguide with a comparatively large cross section, or a bundle of optical fibers.
  • the one or more optical waveguides serve to forward the radiation in a stationary part of the gas turbine to a photodetector.
  • optical waveguides By using optical waveguides as a recording device, it is possible to realize the detector in a thermally less stressed region of the gas turbine.
  • the receiving device can also be the photodetector directly. This is then provided to turn gen possible for a lossless recording of thermal radiation to sor ⁇ preferably with a sufficiently large detector surface.
  • the optical waveguide may be designed to be tappered at its corresponding end. This makes it possible to control the area of the surface of the vane from which heat radiation is absorbed.
  • FIG. 2 Variants of the receiving collimator on the sliding display.
  • FIG. 1 shows a section of a gas turbine 10. Here, only parts of the components are shown schematically.
  • the gas turbine 10 comprises a rotor blade 11 and Leitschau- fine 12.
  • the rotor blade 11 is rotatably mounted on a shaft 17.
  • the vanes 12 are fixed to the housing ⁇ arranged and do not rotate during operation.
  • a glass fiber 13 is embedded in the blade 11. It runs from one to the surface of the blade
  • a lens collimator 14 located end into the shaft 17 inside. The end located on the surface of the blade 11 points in the direction of the guide vanes 12. At the end of the optical waveguide 13 there is provided a lens collimator 14.
  • the other end of the glass fiber 13 lies on a surface of the shaft 17.
  • the glass fiber 13 terminates there with a second collimator 18.
  • the second collimator 18 is designed so that the emitted radiation exits in an axial Pa ⁇ rallelstrahl.
  • the radiation thus emitted impinges on a photodetector 20, the receiving surface of which is designed over a large area in comparison to the cross section of the glass fiber 13.
  • FIG. 2 shows variants for the termination of the glass fiber 13 which points in the direction of the guide vanes 12.
  • the optical fiber 13 may be terminated with the lens collimator 14.
  • Another possibility and alternative is to terminate the fiberglass
  • the glass fiber has a taped end 22 on ⁇ .
  • Another alternative is to use a low aperture glass fiber 13. Then this end 21 of the glass fiber 13 without special design.
  • an area 16 sends a vane
  • the region 16 is small compared to the size of the guide blade 12.
  • the thermal radiation enters the glass fiber 13 via the lens collimator 14. It is routed there to its other end and enters the photodetector 20 through the second collimator 18 and the following air gap.
  • the electrical signals which are triggered by the radiation 19 are evaluated and the temperature of the region 16 thus determined.
  • the rotor blade 11 rotates.
  • the glass fiber 13 of course rotates with it.
  • the area 16 of the vane 12 thereby travels around the shaft 17 in a circular path. Since this movement is relatively fast, the temperature of each region 16 of the vane 12 lying on the circular path can be viewed virtually at all times. For this purpose, it is only necessary to wait for a single sweep of the blade 11 over the desired region 16.
  • the temporal resolution of the evaluation determines which angular section of the circular path is ultimately regarded as area 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Radiation Pyrometers (AREA)

Abstract

L'invention concerne une turbine à gaz comportant au moins une aube directrice fixe et au moins une aube mobile qui tourne en service et possédant au moins un guide d'ondes noyé dans une première aube mobile. Le guide d'ondes est conçu pour que le rayonnement thermique d'une zone de la première aube directrice soit capté par le guide d'ondes. Un dispositif d'analyse est conçu pour analyser le rayonnement thermique et pour déterminer la température de la zone de la première aube directrice, la température pouvant être déterminée sur une course dont provient le rayonnement thermique du fait de la rotation de la première aube mobile.
PCT/EP2012/060209 2011-06-21 2012-05-31 Turbine à gaz dotée d'un pyromètre Ceased WO2012175302A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12726080.0A EP2723994A1 (fr) 2011-06-21 2012-05-31 Turbine à gaz dotée d'un pyromètre
US14/126,437 US20140133994A1 (en) 2011-06-21 2012-05-31 Gas turbine with pyrometer
JP2014516256A JP2014522964A (ja) 2011-06-21 2012-05-31 パイロメータを備えたガスタービン

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011077908.6 2011-06-21
DE102011077908A DE102011077908A1 (de) 2011-06-21 2011-06-21 Gasturbine mit Pyrometer

Publications (1)

Publication Number Publication Date
WO2012175302A1 true WO2012175302A1 (fr) 2012-12-27

Family

ID=46210236

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/060209 Ceased WO2012175302A1 (fr) 2011-06-21 2012-05-31 Turbine à gaz dotée d'un pyromètre

Country Status (5)

Country Link
US (1) US20140133994A1 (fr)
EP (1) EP2723994A1 (fr)
JP (1) JP2014522964A (fr)
DE (1) DE102011077908A1 (fr)
WO (1) WO2012175302A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3336497A1 (fr) 2016-12-13 2018-06-20 Siemens Aktiengesellschaft Aube de turbine à gaz comprenant une sonde pyrométrique intégrée

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016010402A1 (de) 2015-09-01 2017-03-02 Sew-Eurodrive Gmbh & Co Kg Anordnung zur Bestimmung der Oberflächentemperatur
US10830132B2 (en) * 2016-04-29 2020-11-10 General Electric Company Micro thermal imaging system for turbine engines

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB972394A (en) * 1962-01-10 1964-10-14 Rolls Royce Gas turbine engine
US4582426A (en) * 1982-12-24 1986-04-15 Rolls-Royce Limited Optical radiation pyrometer
EP0898158A2 (fr) * 1997-08-21 1999-02-24 Abb Research Ltd. Pyromètre optique pour une turbine à gaz
WO1999054692A2 (fr) * 1998-04-14 1999-10-28 Advanced Fuel Research, Inc. Thermometre a rayonnement infrarouge grande vitesse, systeme et procede

Family Cites Families (17)

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US3623368A (en) * 1970-03-09 1971-11-30 Comstock & Wescott Turbine engine blade pyrometer
JPS5920843B2 (ja) * 1980-12-12 1984-05-16 工業技術院長 タ−ビン動翼の異常検出装置
JPS61200437A (ja) * 1985-03-01 1986-09-05 Hitachi Ltd タ−ビンロ−タ温度測定装置
GB9018457D0 (en) * 1990-08-22 1990-10-03 Rolls Royce Plc Flow control means
JP3484477B2 (ja) * 1993-03-16 2004-01-06 川崎重工業株式会社 ガスタービン機関の温度検出方法および温度検出装置
JPH0683928U (ja) * 1993-05-13 1994-12-02 石川島播磨重工業株式会社 タービン静翼の冷却制御装置
JPH0815042A (ja) * 1994-06-28 1996-01-19 Toshiba Corp ガスタービンの作動ガス温度測定装置
JP3569000B2 (ja) * 1994-09-12 2004-09-22 株式会社東芝 ガスタービン翼異常監視システム
GB2370632B (en) * 2000-11-30 2004-11-17 Rolls Royce Plc A gas turbine engine guide vane and temperature monitor therefor
JP2002303103A (ja) * 2001-03-30 2002-10-18 Toshiba Corp 発電プラントの健全性監視装置
JP2005214661A (ja) * 2004-01-27 2005-08-11 Toshiba Corp 発電機器の監視システム
JP4474989B2 (ja) * 2004-04-26 2010-06-09 株式会社Ｉｈｉ タービンノズル及びタービンノズルセグメント
US7095221B2 (en) * 2004-05-27 2006-08-22 Siemens Aktiengesellschaft Doppler radar sensing system for monitoring turbine generator components
KR100760510B1 (ko) * 2006-05-26 2007-09-20 한국과학기술연구원 회전체의 이상감지장치
US7527471B2 (en) * 2006-07-31 2009-05-05 General Electric Company Stator vane and gas turbine engine assembly including same
DE102007020059B4 (de) * 2007-04-27 2014-10-09 Siemens Aktiengesellschaft Verfahren und Vorrichtung zur Ermittlung der Position zumindest eines Teils eines medizinischen Instruments
DE102008022571A1 (de) * 2008-05-07 2010-02-25 Siemens Aktiengesellschaft Temperaturmessung an Teilen einer Strömungsmaschine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB972394A (en) * 1962-01-10 1964-10-14 Rolls Royce Gas turbine engine
US4582426A (en) * 1982-12-24 1986-04-15 Rolls-Royce Limited Optical radiation pyrometer
EP0898158A2 (fr) * 1997-08-21 1999-02-24 Abb Research Ltd. Pyromètre optique pour une turbine à gaz
WO1999054692A2 (fr) * 1998-04-14 1999-10-28 Advanced Fuel Research, Inc. Thermometre a rayonnement infrarouge grande vitesse, systeme et procede

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3336497A1 (fr) 2016-12-13 2018-06-20 Siemens Aktiengesellschaft Aube de turbine à gaz comprenant une sonde pyrométrique intégrée
WO2018108458A1 (fr) 2016-12-13 2018-06-21 Siemens Aktiengesellschaft Aube de turbine à gaz à sonde pyrométrique intégrée

Also Published As

Publication number Publication date
US20140133994A1 (en) 2014-05-15
JP2014522964A (ja) 2014-09-08
DE102011077908A1 (de) 2012-12-27
EP2723994A1 (fr) 2014-04-30

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