US20140133994A1 - Gas turbine with pyrometer - Google Patents

Gas turbine with pyrometer Download PDF

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Publication number
US20140133994A1
US20140133994A1 US14/126,437 US201214126437A US2014133994A1 US 20140133994 A1 US20140133994 A1 US 20140133994A1 US 201214126437 A US201214126437 A US 201214126437A US 2014133994 A1 US2014133994 A1 US 2014133994A1
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US
United States
Prior art keywords
gas turbine
optical waveguide
rotor blade
radiation
collimator
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.)
Abandoned
Application number
US14/126,437
Other languages
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
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOSSELMANN, THOMAS, WILLSCH, MICHAEL
Publication of US20140133994A1 publication Critical patent/US20140133994A1/en
Abandoned legal-status Critical Current

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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
    • 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

  • the invention relates to a gas turbine having at least one stationary stator blade and at least one rotor blade which can be rotated during operation.
  • stator blades Owing to their fixed position relative to the burners, the stationary blades, called stator blades, have larger inhomogeneities in the temperature distribution than the rotor blades, which rotate during operation. The temperature distribution in the stator blades is therefore of great interest. To date, the temperature of the stator blades has been measured in a punctiform manner with the aid of a limited number of stationary thermoelements.
  • the gas turbine comprises at least one stationary stator blade and at least one rotor blade which can be rotated during operation. Also present is at least one optical waveguide, which is embedded in a first rotor blade and is aligned such that thermal radiation of a first stator blade can be detected by the optical waveguide.
  • the gas turbine also comprises an evaluation device for evaluating thermal radiation.
  • the evaluation device is configured to determine the temperature of at least the first stator blade, it being possible to determine the temperature along a path from which the thermal radiation is detected in the course of the rotation of the first rotor blade and thus of the optical waveguide.
  • the region of the stator blade whose thermal radiation is recorded is in this case a function of the optical waveguide and of the distance of the optical waveguide end from the stator blade.
  • the pyrometer which is represented by the optical waveguide, rotates together with a rotor blade and is directed toward a stator blade.
  • the temperature of the stator blade can therefore advantageously no longer be determined only at fixed points at which thermal elements are provided, but at any point on a circular track which results from the movement of the rotor blade relative to the stator blade.
  • the temperature distribution of the stator blade can thus be detected much more accurately than previously.
  • the first rotor blade comprises a photodetector for converting the thermal radiation into electrical signals.
  • the photodetector is expediently coupled to the optical waveguide in order to be able to detect the thermal radiation, which comes from the first stator blade, after passage through the optical waveguide.
  • the photodetector can, for example, be fed in this case by wireless energy transfer.
  • the photodetector can be fed by means of a battery.
  • the pyrometer is advantageously implemented thereby substantially in the rotor blade itself. The data determined can then be recorded and/or passed on by telemetry or by a corotating data plotter.
  • the optical waveguide is guided into the shaft of the first rotor blade and terminates there. It is possible through this configuration for the recorded thermal radiation to be output in the direction of stationary parts of the gas turbine. Said radiation can be more simply recorded and further processed there. It is then advantageous when the end of the optical waveguide in the shaft is provided with a collimator. In accordance with an advantageous refinement of an embodiment, it is possible hereby for the emerging thermal radiation to be emitted in an axial parallel beam. This enables the radiation to be recorded as far as possible without attenuation after traversing a short air gap.
  • the radiation coming from the collimator is detected with the aid of a detection device, wherein the reception range of the detection device is formed over so large an area that substantially all radiation coming from the collimator can be detected.
  • the comparatively large area of the configuration of the detection device enables the thermal radiation to be detected and further processed without attenuation. The accuracy of the measurement is thereby ensured.
  • the detection device is an optical waveguide, in particular an optical waveguide with a comparatively large cross section, or a bundle of optical waveguides.
  • the optical waveguide/waveguides serves/serve to pass on radiation in a stationary part of the gas turbine to a photodetector.
  • the use of optical waveguides as detection device enables the detector to be implemented in a thermally less stressed region of the gas turbine.
  • the detection device can also directly be the photodetector.
  • Said photodetector is then preferably provided with a sufficiently large detector area in order, in turn, to provide as far as possible for attenuation-free recording of the thermal radiation.
  • a lens collimator is provided in the region of the end of the optical waveguide reaching the first stator blade.
  • the optical waveguide can be configured in a tapered fashion at its appropriate end. It is thereby possible to control the region of the surface of the stator blade from which thermal radiation is recorded.
  • FIG. 1 shows an arrangement of the rotating pyrometer in principle
  • FIG. 2 shows variants of the receiving collimator on the rotor blade.
  • FIG. 1 shows a section of a gas turbine 10 . This means that only parts of the components are schematized.
  • the gas turbine 10 comprises a rotor blade 11 and stator blades 12 .
  • the rotor blade 11 is arranged rotatably on a shaft 17 .
  • the stator blades 12 are arranged fixed to the housing and do not rotate during operation.
  • a glass fiber 13 is embedded in the rotor blade 11 . It runs therein from an end situated on the surface of the rotor blade 11 into the shaft 17 . The end situated on the surface of the rotor blade 11 points in the direction of the stator blades 12 .
  • a lens collimator 14 Provided at the end of the optical waveguide 13 there is 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 configured in this case such that the output radiation emerges in an axial parallel beam. The radiation thus output enters a photodetector 20 whose receiving surface has a large area by comparison with the cross section of the glass fiber 13 .
  • FIG. 2 shows variants of the termination of the glass fiber 13 , which points in the direction of the stator blades 12 .
  • the glass fiber 13 can be terminated with the lens collimator 14 .
  • a further possibility and alternative consists in terminating the glass fiber 13 in such a way that the glass fiber has a tapered end 22 .
  • a further alternative consists in using a glass fiber 13 of lower aperture. Said end 21 of the glass fiber 13 then has no special configuration.
  • a region 16 of a stator blade 12 emits thermal radiation in accordance with its temperature.
  • the region 16 is small by comparison with the size of the stator blade 12 .
  • the thermal radiation enters the glass fiber 13 via the lens collimator 14 . It is led there up to its other end and enters the photodetector 20 through the second collimator 18 and the following air gap.
  • the electrical signals initiated by the radiation 19 are evaluated, and the temperature of the region 16 is thereby determined.
  • the rotor blade 11 rotates during operational running.
  • the glass fiber 13 necessarily co-rotates in this case.
  • the region 16 of the stator blade 12 that is under consideration thereby travels around the shaft 17 on a circular track. Since said movement is relatively quick, it is possible at practically any time to consider the temperature of each region 16 of the stator blade 12 which lies on the circular track. All that this requires is to wait until the rotor blade 11 has passed once over the desired region 16 .
  • the temporal resolution of the evaluation in this case determines which angular section of the circular path will ultimately be regarded as region 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)
US14/126,437 2011-06-21 2012-05-31 Gas turbine with pyrometer Abandoned US20140133994A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102011077908A DE102011077908A1 (de) 2011-06-21 2011-06-21 Gasturbine mit Pyrometer
DE102011077908.6 2011-06-21
PCT/EP2012/060209 WO2012175302A1 (fr) 2011-06-21 2012-05-31 Turbine à gaz dotée d'un pyromètre

Publications (1)

Publication Number Publication Date
US20140133994A1 true US20140133994A1 (en) 2014-05-15

Family

ID=46210236

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/126,437 Abandoned US20140133994A1 (en) 2011-06-21 2012-05-31 Gas turbine with pyrometer

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
US20170314464A1 (en) * 2016-04-29 2017-11-02 General Electric Company Micro thermal imaging system for turbine engines

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
EP3336497A1 (fr) 2016-12-13 2018-06-20 Siemens Aktiengesellschaft Aube de turbine à gaz comprenant une sonde pyrométrique intégrée

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3623368A (en) * 1970-03-09 1971-11-30 Comstock & Wescott Turbine engine blade pyrometer
US5230603A (en) * 1990-08-22 1993-07-27 Rolls Royce Plc Control of flow instabilities in turbomachines
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
US6109783A (en) * 1997-08-21 2000-08-29 Abb Research Ltd. Optic pyrometer for gas turbines
US6364524B1 (en) * 1998-04-14 2002-04-02 Advanced Fuel Research, Inc High speed infrared radiation thermometer, system, and method
US6513971B2 (en) * 2000-11-30 2003-02-04 Rolls-Royce Plc Heatable member and temperature monitor therefor
US7083384B2 (en) * 2004-05-27 2006-08-01 Siemens Aktiengesellschaft Doppler radar sensing system for monitoring turbine generator components
US20080285720A1 (en) * 2007-04-27 2008-11-20 Siemens Aktiengesellschaft Method and device for determining a position of a part of a medical instrument
US7495750B2 (en) * 2006-05-26 2009-02-24 Korea Institute Of Science And Technology Monitoring device for rotating body

Family Cites Families (12)

* 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
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
GB2134251B (en) * 1982-12-24 1986-09-17 Rolls Royce Optical radiation pyrometer
JPS61200437A (ja) * 1985-03-01 1986-09-05 Hitachi Ltd タ−ビンロ−タ温度測定装置
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
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
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
US7527471B2 (en) * 2006-07-31 2009-05-05 General Electric Company Stator vane and gas turbine engine assembly including same
DE102008022571A1 (de) * 2008-05-07 2010-02-25 Siemens Aktiengesellschaft Temperaturmessung an Teilen einer Strömungsmaschine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3623368A (en) * 1970-03-09 1971-11-30 Comstock & Wescott Turbine engine blade pyrometer
US5230603A (en) * 1990-08-22 1993-07-27 Rolls Royce Plc Control of flow instabilities in turbomachines
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
US6109783A (en) * 1997-08-21 2000-08-29 Abb Research Ltd. Optic pyrometer for gas turbines
US6364524B1 (en) * 1998-04-14 2002-04-02 Advanced Fuel Research, Inc High speed infrared radiation thermometer, system, and method
US6513971B2 (en) * 2000-11-30 2003-02-04 Rolls-Royce Plc Heatable member and temperature monitor therefor
US7083384B2 (en) * 2004-05-27 2006-08-01 Siemens Aktiengesellschaft Doppler radar sensing system for monitoring turbine generator components
US7495750B2 (en) * 2006-05-26 2009-02-24 Korea Institute Of Science And Technology Monitoring device for rotating body
US20080285720A1 (en) * 2007-04-27 2008-11-20 Siemens Aktiengesellschaft Method and device for determining a position of a part of a medical instrument

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170314464A1 (en) * 2016-04-29 2017-11-02 General Electric Company Micro thermal imaging system for turbine engines
US10830132B2 (en) * 2016-04-29 2020-11-10 General Electric Company Micro thermal imaging system for turbine engines

Also Published As

Publication number Publication date
EP2723994A1 (fr) 2014-04-30
DE102011077908A1 (de) 2012-12-27
WO2012175302A1 (fr) 2012-12-27
JP2014522964A (ja) 2014-09-08

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AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOSSELMANN, THOMAS;WILLSCH, MICHAEL;REEL/FRAME:031783/0980

Effective date: 20131202

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION