EP2870439A2 - Procédé de surveillance du fonctionnement d'une turbine à gaz - Google Patents

Procédé de surveillance du fonctionnement d'une turbine à gaz

Info

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Withdrawn
Application number
EP13745023.5A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Peter Kaufmann
Tobias Krieger
Jaap Van Kampen
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 Energy Global GmbH and Co KG
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
Publication of EP2870439A2 publication Critical patent/EP2870439A2/fr
Withdrawn legal-status Critical Current

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.

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Turbines (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
  • Testing Of Engines (AREA)

Abstract

L'invention concerne un procédé de surveillance du fonctionnement d'une turbine à gaz (10). Un capteur d'accélération (40) disposé sur un composant permet de détecter les vibrations de ce composant pendant le fonctionnement de la turbine à gaz (10). A partir du signal (39) fourni par le capteur d'accélération (40) et traité, on détermine plusieurs segments de signal au moyen de plusieurs bandes de fréquence (fb). L'invention vise à éviter un arrêt inutile de la turbine à gaz (10) afin de procéder à une inspection a posteriori inutile et donc à accroître ainsi la disponibilité de la turbine à gaz (10). A cet effet, on détermine une durée de vibration totale en additionnant les durées de vibration des segments de signal pendant lesquels l'amplitude des segments de signal concernés est supérieure à une valeur limite spécifique à la bande de fréquence.
EP13745023.5A 2012-08-30 2013-07-25 Procédé de surveillance du fonctionnement d'une turbine à gaz Withdrawn EP2870439A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012215410 2012-08-30
PCT/EP2013/065732 WO2014032875A2 (fr) 2012-08-30 2013-07-25 Procédé de surveillance du fonctionnement d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2870439A2 true EP2870439A2 (fr) 2015-05-13

Family

ID=48916019

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13745023.5A Withdrawn EP2870439A2 (fr) 2012-08-30 2013-07-25 Procédé de surveillance du fonctionnement d'une turbine à gaz

Country Status (7)

Country Link
US (1) US10241006B2 (fr)
EP (1) EP2870439A2 (fr)
JP (1) JP2015529768A (fr)
KR (1) KR20150047497A (fr)
CN (1) CN104620085A (fr)
RU (1) RU2015111210A (fr)
WO (1) WO2014032875A2 (fr)

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ES2790473T3 (es) * 2014-08-04 2020-10-27 Tlv Co Ltd Sistema de monitorización de equipos, programa de monitorización de equipos, y método de monitorización de equipos
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 (fr) * 2018-03-20 2019-09-25 Siemens Aktiengesellschaft Brûleur pour turbine à gaz et procédé d'exploitation du brûleur
CN110530507B (zh) * 2019-08-29 2021-10-15 郑州大学 用于旋转设备监测的边缘计算方法、介质及系统
CN110726471A (zh) * 2019-11-28 2020-01-24 中国华能集团有限公司 一种适用于燃气轮机燃烧室振动的监测装置及监测方法
CN114484495B (zh) * 2022-04-18 2022-07-01 北京航空航天大学 基于金属粒子添加的热声振荡主动控制装置

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US5069071A (en) * 1990-08-27 1991-12-03 United Technologies Corporation Vibration monitoring in the frequency domain with a capacitive accelerometer
DE4032299A1 (de) 1990-10-11 1992-04-16 Siemens Ag Verfahren und einrichtung zum ueberwachen eines drehbaren bauteiles
DE4124302A1 (de) 1991-07-23 1993-01-28 Hoesch Stahl Ag Verfahren zur erkennung und auswertung von schwingungsanregungen oder schwingungsaehnlicher zustaende
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 (de) * 2002-02-22 2006-04-20 Framatome Anp Gmbh Verfahren und Einrichtung zur Detektion einer impulsartigen mechanischen Einwirkung auf ein Anlagenteil
JP2003293794A (ja) * 2002-04-05 2003-10-15 Mitsubishi Heavy Ind Ltd ガスタービン制御装置、ガスタービンシステム及びガスタービン遠隔監視システム
JP2003293793A (ja) * 2002-04-05 2003-10-15 Mitsubishi Heavy Ind Ltd 燃焼振動予兆検知装置、ガスタービンシステム及び燃焼振動予兆検知方法
JP2003314305A (ja) * 2002-04-24 2003-11-06 Mitsubishi Heavy Ind Ltd ガスタービン制御装置、ガスタービンシステム及びガスタービン制御方法
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Also Published As

Publication number Publication date
WO2014032875A2 (fr) 2014-03-06
CN104620085A (zh) 2015-05-13
US20150204760A1 (en) 2015-07-23
KR20150047497A (ko) 2015-05-04
US10241006B2 (en) 2019-03-26
RU2015111210A (ru) 2016-10-20
JP2015529768A (ja) 2015-10-08
WO2014032875A3 (fr) 2014-06-12

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