EP2870439A2 - Method for monitoring the operation of a gas turbine - Google Patents
Method for monitoring the operation of a gas turbineInfo
- Publication number
- EP2870439A2 EP2870439A2 EP13745023.5A EP13745023A EP2870439A2 EP 2870439 A2 EP2870439 A2 EP 2870439A2 EP 13745023 A EP13745023 A EP 13745023A EP 2870439 A2 EP2870439 A2 EP 2870439A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- signal
- component
- acceleration sensor
- oscillation period
- 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.)
- Withdrawn
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
- G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
Definitions
- the invention relates to a method for monitoring the operation of a gas turbine, wherein component vibrations are detected by an acceleration sensor arranged on the component during operation of the gas turbine, and the signal forwarded by the acceleration sensor is detected by means of a plurality of frequency bands determined.
- Vibrations occur with an amplitude exceeding the associated limit, a warning is displayed to the gas turbine operator and, if necessary, an emergency shutdown of the gas turbine performed to the combustion chambers To protect against the component damaging vibrations.
- the skilled person calls this shutdown as "Trip”.
- combustion chambers in particular hardened annular combustion chambers, are subjected to a visual inspection at regular time intervals during an inspection. This should be detected early on such defects. In the presence of defects then the damaged components or components are replaced.
- the visual inspection of the gas turbine requires downtime, which reduces the availability of the gas turbine.
- the object of the invention is therefore to provide a method for monitoring the operation of a gas turbine, in which previously unnecessary stoppages of the gas turbine for visual inspections can be avoided.
- the method according to the invention for monitoring the operation of a gas turbine in which component vibrations are detected by an acceleration sensor arranged on the component during operation of the gas turbine and that from a signal representing the accelerations, which is located on the signal from the Acceleration sensor forwarded signal is divided by a frequency band or by means of several frequency bands in a signal section (s), provides that a total oscillation period is determined by a count of those time intervals in which the largest amplitudes in individual signal sections are greater than an associated frequency band specific limit.
- the component is preferably designed as a combustion chamber, so that combustion chamber oscillations and / or combustion chamber accelerations are detected by the sensor arranged thereon.
- the signal provided by the sensor is then processed by means of a Fourier transformation at short time intervals-which are generally less than one second-and then further processed as a signal representing the accelerations for this short time interval.
- the counter is compared with a limit value or the total vibration duration with a total vibration duration limit value and, when the overall vibration duration limit value is exceeded, an inspection of the gas turbine, maintenance of the gas turbine and / or replacement of gas turbine components is performed.
- FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
- the gas turbine 10 has inside a rotatably mounted about an axis of rotation 12 rotor 14, which is also referred to as a turbine runner.
- a turbine runner Along the rotor 14 successive an intake housing 16, a Axialturbover Noticer 18, a toroidal annular combustion chamber 20 with a plurality of rotationally symmetrical mutually arranged burners 22, a turbine unit 24 and a turbine outlet housing 26th
- the axial turbo-compressor 18 comprises an annularly shaped compressor channel 25 with compressor stages of rotor blade and guide blade rings which follow one another in cascade.
- the rotor blades 14 arranged on the blades 27 lie with their free-ending blade tips 29 a outer channel wall 42 of the compressor passage 25 opposite.
- the compressor channel 25 opens via a
- Compressor outlet diffuser 36 in a plenum 38 therein, the annular combustion chamber 20 is provided with its combustion chamber 28, which communicates with an annular hot gas channel 30 of the turbine unit 24. In the turbine unit 24 four successive turbine stages 32 are arranged. On the rotor 14, a generator or a working machine (each not shown) is coupled.
- the axial turbocharger 18 draws in ambient air 34 through the intake housing 16 as a medium to be compressed and compresses it.
- the compressed air is guided through the compressor outlet diffuser 36 into the plenum 38, from where it flows into the burner 22.
- Fuel also passes into the combustion space 28 via the burners 22. There, the fuel is burned to a hot gas M with the addition of the compressed air.
- the hot gas M then flows into the hot gas duct 30, where it relaxes to perform work on the turbine blades of the turbine unit 24.
- the signal section occurring in the frequency band fb 34 has the greatest amplitude for the acceleration of the annular combustion chamber 20 as a component of the gas turbine 10 to be monitored.
- the conditioned signal 39 does not have to be completely divided into immediately successive signal sections.
- a total vibration duration should be determined.
- the signal section of a frequency band or the respective signal sections of a plurality of frequency bands of the time-varying conditioned signal 39 of the acceleration sensor 40 is continuously monitored. If the amplitude (n) of the respective signal sections currently occurring in the frequency band fb or in the several frequency bands fb is greater than a frequency band-specific limit value GW, the time duration for which the amplitudes of the meeting signal sections are greater than the associated frequency band-specific limit value GW, the total oscillation added up. This applies to every considered frequency band fb.
- the invention is based on the recognition that not every greater amplitude of an acceleration of the monitored component - usually the annular combustion chamber 20 - is detrimental to the component in question, remain some signal portions of the processed signal 39 of the acceleration sensor 40, which are therefore outside the frequency bands fb, disregarded.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102012215410 | 2012-08-30 | ||
PCT/EP2013/065732 WO2014032875A2 (en) | 2012-08-30 | 2013-07-25 | Method for monitoring the operation of a gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2870439A2 true EP2870439A2 (en) | 2015-05-13 |
Family
ID=48916019
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13745023.5A Withdrawn EP2870439A2 (en) | 2012-08-30 | 2013-07-25 | Method for monitoring the operation of a gas turbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US10241006B2 (en) |
EP (1) | EP2870439A2 (en) |
JP (1) | JP2015529768A (en) |
KR (1) | KR20150047497A (en) |
CN (1) | CN104620085A (en) |
RU (1) | RU2015111210A (en) |
WO (1) | WO2014032875A2 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
AT18087U1 (en) * | 2014-08-04 | 2024-01-15 | Tlv Co Ltd | EQUIPMENT MONITORING SYSTEM, EQUIPMENT MONITORING PROGRAM AND EQUIPMENT MONITORING METHOD |
US9530291B2 (en) * | 2014-09-19 | 2016-12-27 | General Electric Company | Systems and methods for providing qualitative indication of vibration severity while recording |
US10626749B2 (en) * | 2016-08-31 | 2020-04-21 | General Electric Technology Gmbh | Spindle vibration evaluation module for a valve and actuator monitoring system |
EP3543608A1 (en) * | 2018-03-20 | 2019-09-25 | Siemens Aktiengesellschaft | Burner for a gas turbine and method for operating the burner |
CN110530507B (en) * | 2019-08-29 | 2021-10-15 | 郑州大学 | Edge calculation method, medium, and system for monitoring rotating device |
CN110726471A (en) * | 2019-11-28 | 2020-01-24 | 中国华能集团有限公司 | Monitoring device and monitoring method suitable for vibration of combustion chamber of gas turbine |
CN114484495B (en) * | 2022-04-18 | 2022-07-01 | 北京航空航天大学 | Thermoacoustic oscillation active control device based on metal particle addition |
Family Cites Families (22)
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US4887468A (en) | 1988-06-03 | 1989-12-19 | Westinghouse Electic Corp. | Nonsynchronous turbine blade vibration monitoring system |
US5069071A (en) * | 1990-08-27 | 1991-12-03 | United Technologies Corporation | Vibration monitoring in the frequency domain with a capacitive accelerometer |
DE4032299A1 (en) | 1990-10-11 | 1992-04-16 | Siemens Ag | Monitoring rotatable component esp. rotor shaft - time-dependently measuring oscillatory path of component in radial direction and rotary position |
DE4124302A1 (en) * | 1991-07-23 | 1993-01-28 | Hoesch Stahl Ag | Detecting and evaluating vibration sources in machinery - dividing into frequency bands, rectifying, smoothing, and feeding large amplitude signals or dynamically varying signals to regulator for acoustic or visual indication |
US5445028A (en) | 1992-09-18 | 1995-08-29 | Ametek Aerospace Products Inc. | Dynamic digital tracking filter |
US6354071B2 (en) * | 1998-09-25 | 2002-03-12 | General Electric Company | Measurement method for detecting and quantifying combustor dynamic pressures |
DE10207455B4 (en) * | 2002-02-22 | 2006-04-20 | Framatome Anp Gmbh | Method and device for detecting a pulse-like mechanical action on a plant part |
JP2003293794A (en) * | 2002-04-05 | 2003-10-15 | Mitsubishi Heavy Ind Ltd | Gas turbine control device, gas turbine system, and gas turbine remote monitoring system |
JP2003293793A (en) * | 2002-04-05 | 2003-10-15 | Mitsubishi Heavy Ind Ltd | Combustion vibration sign detector, gas turbine system, and combustion vibration sign detection method |
JP2003314305A (en) * | 2002-04-24 | 2003-11-06 | Mitsubishi Heavy Ind Ltd | Gas turbine control device, gas turbine system, and gas turbine control method |
JP3930371B2 (en) * | 2002-04-24 | 2007-06-13 | 三菱重工業株式会社 | Gas turbine control device, gas turbine system, and gas turbine control method |
JP2005155590A (en) * | 2003-10-30 | 2005-06-16 | Mitsubishi Heavy Ind Ltd | Gas turbine control apparatus, gas turbine system and gas turbine control method |
EP1582694A1 (en) * | 2004-04-02 | 2005-10-05 | Siemens Aktiengesellschaft | Method for protecting openings in a component during processing |
JP4592513B2 (en) * | 2004-09-30 | 2010-12-01 | 三菱重工業株式会社 | Gas turbine control device and gas turbine system |
FR2913769B1 (en) * | 2007-03-12 | 2009-06-05 | Snecma Sa | METHOD FOR DETECTING DAMAGE TO A BEARING BEARING OF AN ENGINE |
ITMI20071048A1 (en) * | 2007-05-23 | 2008-11-24 | Nuovo Pignone Spa | METHOD FOR THE CONTROL OF THE PRESSURE DYNAMICS AND FOR THE ESTIMATE OF THE LIFE CYCLE OF THE COMBUSTION CHAMBER OF A GAS TURBINE |
JP5010502B2 (en) * | 2008-02-28 | 2012-08-29 | 三菱重工業株式会社 | Gas turbine control method and apparatus |
KR100903949B1 (en) * | 2008-05-09 | 2009-06-25 | 한국지질자원연구원 | Method for predicting failure of geotechnical structure |
JP4995169B2 (en) * | 2008-09-29 | 2012-08-08 | 三菱重工業株式会社 | Gas turbine control method and apparatus |
WO2010131190A2 (en) * | 2009-05-13 | 2010-11-18 | Koninklijke Philips Electronics N.V. | An active pillow system and a method for manipulating a person's resting conditions |
FR2956481B1 (en) * | 2010-02-18 | 2012-02-10 | Snecma | METHOD FOR DETECTING RESONANCE OF A ROTOR SHAFT OF A TURBOMOTEUR |
US9255835B2 (en) * | 2012-08-22 | 2016-02-09 | Siemens Energy, Inc. | System for remote vibration detection on combustor basket and transition in gas turbines |
-
2013
- 2013-07-25 WO PCT/EP2013/065732 patent/WO2014032875A2/en active Application Filing
- 2013-07-25 US US14/423,715 patent/US10241006B2/en not_active Expired - Fee Related
- 2013-07-25 JP JP2015528925A patent/JP2015529768A/en active Pending
- 2013-07-25 CN CN201380047002.XA patent/CN104620085A/en active Pending
- 2013-07-25 KR KR1020157004744A patent/KR20150047497A/en not_active Application Discontinuation
- 2013-07-25 EP EP13745023.5A patent/EP2870439A2/en not_active Withdrawn
- 2013-07-25 RU RU2015111210A patent/RU2015111210A/en unknown
Non-Patent Citations (2)
Title |
---|
None * |
See also references of WO2014032875A2 * |
Also Published As
Publication number | Publication date |
---|---|
US10241006B2 (en) | 2019-03-26 |
KR20150047497A (en) | 2015-05-04 |
WO2014032875A3 (en) | 2014-06-12 |
US20150204760A1 (en) | 2015-07-23 |
WO2014032875A2 (en) | 2014-03-06 |
JP2015529768A (en) | 2015-10-08 |
RU2015111210A (en) | 2016-10-20 |
CN104620085A (en) | 2015-05-13 |
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