EP2239505A1 - Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz - Google Patents

Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz Download PDF

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Publication number
EP2239505A1
EP2239505A1 EP09157596A EP09157596A EP2239505A1 EP 2239505 A1 EP2239505 A1 EP 2239505A1 EP 09157596 A EP09157596 A EP 09157596A EP 09157596 A EP09157596 A EP 09157596A EP 2239505 A1 EP2239505 A1 EP 2239505A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
tendency
value
stability parameter
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Withdrawn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
EP09157596A
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German (de)
English (en)
Inventor
Malte Blomeyer
Eberhard Deuker
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 EP09157596A priority Critical patent/EP2239505A1/fr
Priority to ES10713903T priority patent/ES2700444T3/es
Priority to PCT/EP2010/054585 priority patent/WO2010115921A2/fr
Priority to RU2011145037/06A priority patent/RU2548233C2/ru
Priority to EP10713903.2A priority patent/EP2417395B1/fr
Priority to CN201080015017.4A priority patent/CN102713438B/zh
Publication of EP2239505A1 publication Critical patent/EP2239505A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/242—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

Definitions

  • the invention relates to a method for analyzing the tendency to hum of a combustion chamber and a method for controlling the operation of a gas turbine with a combustion chamber, provided that hum of the combustion chamber is prevented.
  • combustion chamber hum When combustion of a combustion air / fuel mixture in a combustion chamber, in particular in a combustion chamber of a gas turbine, it may lead to the formation of combustion oscillations.
  • the occurrence of combustion oscillations is also known as "combustion chamber hum".
  • the combustor of the gas turbine tends to hum when the gas turbine is operated at a high turbine inlet temperature to achieve high thermal efficiency of the gas turbine.
  • the high turbine inlet temperature can be achieved by a correspondingly high combustion temperature in the combustion chamber, whereby the combustion chamber tends to hum.
  • Remedy is the operation of the gas turbine with sufficient distance from the limit of self-excited combustion oscillations.
  • the limit of the self-excited combustion vibrations can unfavorably shift, so that for the most unfavorable environmental conditions, a sufficient distance from the limit of self-excited combustion vibrations must be maintained. It is disadvantageous that thus the upper power range of the gas turbine must be excluded and can not be driven.
  • the object of the invention is to provide a method for analyzing the rumble tendency of a combustion chamber, a method for controlling an operation of a gas turbine with a combustion chamber and a control device for controlling an operation of a gas turbine, the method being able to effectively operate the combustion chamber with sufficiently low rumbling tendency ,
  • the method according to the invention for analyzing the rumble tendency of a combustion chamber in an operating state comprises the steps of: operating the combustion chamber in the operating state; Detecting a thermoacoustic size of the combustion chamber gas volume and / or a vibration magnitude of the combustion chamber structure in the operating state and determining a characteristic from the thermoacoustic variable and / or the vibration magnitude; Determining the spectrum of the characteristic in the operating state as the amplitude characteristic of the parameter over time; Identifying a first resonance and a second resonance of the characteristic using the spectrum; Determining the amplitude value of the first resonance and the amplitude value of the second resonance; Calculating the ratio value from the division of the amplitude value of the first resonance and the amplitude value of the second resonance as a stability parameter; Determine the lower distance value and / or the upper distance value by which the stability parameter is above a lower predetermined threshold and / or below an upper predetermined threshold, wherein the threshold values are selected such that when the combustion chamber is in an operating state with a just barely tolerate
  • the thresholds may be selected depending on the operating and ambient conditions.
  • the magnitude of the amplitude values of the parameter changes moderately with the combustion load of the combustion chamber and is only of limited significance for the analysis of the tendency to hum of the combustion chamber. Reaching the hum limit is often characterized by the fact that the amplitude values suddenly rise very sharply. It is therefore not recognized by the initially moderate course of the amplitude values that one approaches dangerously close to the hum. If the amplitudes rise suddenly when reaching the hum limit (usually in fractions of a second), the gas turbine can only be protected from mechanical damage by drastic measures which are disadvantageous from the point of view of the operator, such as immediate, significant load reduction.
  • approaching the hum limit can be recognized by the fact that the shape of the spectrum of the parameter changes.
  • the ratio of the amplitudes of two frequency bands could be used to quantify the rumbling tendency.
  • the amplitude ratio remains constant when increasing the combustion load (despite the increase in the absolute amplitude values), there is no danger. But if the relationship changes, then one approaches the borderline or moves away from it.
  • By quantifying the rumble tendency a tendency to approach the hum limit can be detected and thus timely countermeasures can be initiated be avoided, so that the reaching of the hum limit, with its adverse consequences for the operation is avoided.
  • the stability parameter is calculated with the ratio value from the division of the amplitude value of the first resonance and the amplitude value of the second resonance.
  • the stability parameter is formed as the logarithm of the ratio. Further, it is preferable that the stability parameter is attenuated over time with a damping function. In this way, excessive transient changes in the stability parameter can advantageously be contained.
  • an attenuation function may be formed such that at a time instant n the stability parameter is formed from the arithmetic mean of the ratio value at time n and the ratio value at time n-1.
  • the characteristic is measured at the same time and for each site the local spectrum is determined, the local spectra having an envelope used as the spectrum.
  • the spectrum formed with the envelope of the entire possibly determined by spatial inhomogeneities operating state of the combustion chamber is represented.
  • the combustion chamber is preferably designed as an annular combustion chamber rotationally symmetrical about an axis and has a plurality of locations at which the characteristics are measured, wherein the number of measurement points is reduced by utilizing the symmetry of waveforms.
  • the parameter is the sound pressure in the combustion chamber and / or the acceleration of the combustion chamber structure.
  • the method according to the invention for controlling an operation of a gas turbine with a combustion chamber comprises the steps of: performing the previous method for analyzing the tendency to hum of the combustion chamber of the gas turbine during its operation; once the quantification of the rumble tendency indicates that the stability parameter has reached at least one of the threshold values, reducing the output power of the gas turbine.
  • the stability parameter can be used directly as a controlled variable for operating the gas turbine.
  • the instantaneous load of the gas turbine is directly correlated to the stability parameter, so that with the stability parameter, a power control of the gas turbine with regard to the averting of the hum of the combustion chamber can be accomplished.
  • the method of controlling the operation of the gas turbine further includes the step of: once the quantification of the rumble tendency indicates that the stability parameter has reached a predetermined distance value to at least one of the threshold values, controlling the operation of the gas turbine to reduce the rumble tendency.
  • the turbine outlet temperature is reduced by changing the compressor air mass flow into the combustion chamber as a manipulated variable from its desired value and / or changes the temperature of the fuel in the combustion chamber as a control variable compared to their desired value is and / or the spatial distribution of the fuel supply is changed in the combustion chamber as a manipulated variable to its desired value.
  • the manipulated variable is preferably reset to its desired value.
  • the method of controlling the operation of the gas turbine comprises the step of, once the quantification of the rumble tendency indicates that the stability parameter has reached a predetermined and low rumble-defining distance value to at least one of the thresholds, controlling the operation of the gas turbine such that the operation the gas turbine is optimized in particular with regard to output power, emission and / or fuel consumption.
  • a control device for controlling an operation of a gas turbine is set up to carry out the aforementioned method.
  • FIG. 1 a coordinate system is shown, in which spectra 1, 1 'and 1 "are plotted, the abscissa axis 4 of the coordinate system shows a frequency in [Hz], with the ordinate axis 5 of the coordinate system showing an amplitude as a dimensionless quantity.
  • the spectra 1, 1 ', 1 are the amplitude characteristics of a parameter over the frequency
  • the characteristic is the sound pressure in a combustion chamber, which occurs during operation of the combustion chamber
  • the sound pressure in the combustion chamber can be measured with one or more microphones in the combustion chamber become.
  • the spectrum 1 results when the Brummneist the combustion chamber is low. If the operating state of the combustion chamber is changed in such a way that the tendency to humming increases, the spectrum 1 changes into the spectrum 1 '. If the operating state of the combustion chamber is further changed, that the rumbling tendency increases and reaches a just yet permissible limit range, the spectrum 1 'changes into the spectrum 1 ".As a first resonance, the spectra 1, 1', 1" first amplitude maximum 2, 2 ', 2 "and as a second resonance a second amplitude maximum 3, 3', 3" on.
  • the natural logarithm of the ratio formed is taken from the first amplitude maximum 2, 2 ', 2 "and the second amplitude maximum 3, 3', 3".
  • FIG. 2 a coordinate system is shown, over whose abscissa 8 the time from 0 to 2 minutes is plotted.
  • the left ordinate 6 is the stability parameter and the right ordinate 7 is a turbine outlet temperature.
  • the curve 10 of the turbine outlet temperature is 579 ° C. This results in the operating state in the combustion chamber, in which the sound pressure prevails, the spectrum of 1 in FIG. 1 is shown.
  • the stability parameter 6 for the spectrum 1 is 0.6, as it is in the in FIG. 2 shown diagram with the curve 9 at the time 0 minutes. Will now be the operation of the gas turbine turbine outlet temperature increases as it does in the 10-minute trajectory FIG.
  • FIG. 2 Furthermore, the course of the acceleration 14 of the combustion chamber structure is shown, which is substantially constant until the turbine outlet temperature 10 is raised to the first level 11. If the turbine outlet temperature 10 is increased to a second level 12, then the course 9 of the stability parameter 6 continues to drop and, in the combustion chamber, finally, hum occurs.
  • the humming has the consequence that the combustion chamber structure is strongly vibrated with the thus self-excited combustion vibrations, whereby the acceleration increases 14 to an acceleration peak 15 abruptly.
  • the acceleration tip 15 is so high that damage to the combustion chamber structure is to be expected. Therefore, to prevent damage to the combustor structure, the gas turbine is shut down resulting in a rapid drop in the turbine discharge temperature curve 10 FIG. 2 shows.
  • a threshold 16 of the stability parameter 6 is plotted at 0.1.
  • the course 9 of the stability parameter 6 falls below (in FIG. 2 17), threshold 16 at a first time 18, which is 1.55 minutes.
  • the first time 18 is advanced 15 seconds from the second point in time 19, when the acceleration peak 15 occurs.
  • the threshold value 16 becomes the stability parameter 6 falls below, it remains in accordance FIG. 2 a reaction time of 15 seconds, during which the operation of the gas turbine is to be changed in such a way to attenuate the rumbling tendency that the hum of the combustion chamber and thus the resulting rapid shutdown of the gas turbine can be avoided.
  • the diagrams in 3 and 4 are similar to the diagram in FIG. 2 and show an operation of the gas turbine under the condition of preventing hum of the combustion chamber.
  • the Brummneist the combustion chamber may increase, for example, that decreases in a compressor of the gas turbine due to wear or contamination, the pressure ratio. Further, the Brummneist the combustion chamber may increase by the fact that the ambient temperature and thus the compressor inlet temperature increases during operation of the gas turbine. For example, let the gas turbine operate at a turbine exhaust temperature level, as does the trajectory 10 at the origin of the abscissa in FIG FIG. 3 shows. Caused by, for example, one of the aforementioned influences, the tendency to hum of the combustion chamber increases, so that the course 9 of the stability parameter 6 drops.
  • a second threshold 16 ' is plotted at 0.2 which is above the first threshold 16 (threshold 16 at 0.1).
  • the fuel supply into the combustion chamber is reduced at a third time 20 by means of a control device for the gas turbine such that the curve 10 of the turbine outlet temperature within 3 seconds at the fourth time 21 7 lowers by 1 Kelvin.
  • the lowering of the curve 9 of the stability parameter 6 is decelerated and vice versa, so that finally the curve 9 of the stability parameter 6 exceeds the threshold value 16 'again at the fifth time point 22.
  • FIG. 4 The diagram shown, the operation of the gas turbine is shown, in which a segregation of the output power of the gas turbine by increasing the turbine outlet temperature 10 is to be achieved.
  • the course 9 of the stability parameter 6 drops until it has reached the threshold value 16 '.
  • the curve 9 'of the stability parameter 6 would be such that the threshold value 16 is reached at 0.1, which would result in an early shutdown of the gas turbine.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Testing Of Engines (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Feeding And Controlling Fuel (AREA)
EP09157596A 2009-04-08 2009-04-08 Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz Withdrawn EP2239505A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP09157596A EP2239505A1 (fr) 2009-04-08 2009-04-08 Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz
ES10713903T ES2700444T3 (es) 2009-04-08 2010-04-07 Procedimiento para analizar la tendencia de zumbido de una cámara de combustión y procedimiento para controlar una turbina de gas
PCT/EP2010/054585 WO2010115921A2 (fr) 2009-04-08 2010-04-07 Procédé d'analyse de la tendance au ronflement d'une chambre de combustion et procédé de commande d'une turbine à gaz
RU2011145037/06A RU2548233C2 (ru) 2009-04-08 2010-04-07 Способ диагностирования склонности камеры сгорания к гудению и способ управления газовой турбиной
EP10713903.2A EP2417395B1 (fr) 2009-04-08 2010-04-07 Procédé d'analyse de la tendance au ronflement d'une chambre de combustion et procédé de commande d'une turbine à gaz
CN201080015017.4A CN102713438B (zh) 2009-04-08 2010-04-07 用于分析燃烧室的轰鸣倾向和控制燃气轮机的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09157596A EP2239505A1 (fr) 2009-04-08 2009-04-08 Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz

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EP2239505A1 true EP2239505A1 (fr) 2010-10-13

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Application Number Title Priority Date Filing Date
EP09157596A Withdrawn EP2239505A1 (fr) 2009-04-08 2009-04-08 Procédé d'analyse de la tendance d'une chambre de combustion à émettre des bruits à basse fréquence et procédé de commande d'une turbine à gaz
EP10713903.2A Active EP2417395B1 (fr) 2009-04-08 2010-04-07 Procédé d'analyse de la tendance au ronflement d'une chambre de combustion et procédé de commande d'une turbine à gaz

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EP10713903.2A Active EP2417395B1 (fr) 2009-04-08 2010-04-07 Procédé d'analyse de la tendance au ronflement d'une chambre de combustion et procédé de commande d'une turbine à gaz

Country Status (5)

Country Link
EP (2) EP2239505A1 (fr)
CN (1) CN102713438B (fr)
ES (1) ES2700444T3 (fr)
RU (1) RU2548233C2 (fr)
WO (1) WO2010115921A2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520863A1 (fr) * 2011-05-05 2012-11-07 Alstom Technology Ltd Procédé de protection d'un moteur à turbine à gaz contre des valeurs de processus dynamique élevées et moteur de turbine à gaz pour l'exécution de ce procédé
EP3045676A1 (fr) 2015-01-13 2016-07-20 Siemens Aktiengesellschaft Procédé destiné à éviter un détachement de courant rotatif
EP3101343A1 (fr) * 2015-06-05 2016-12-07 Siemens Aktiengesellschaft Procede de commande intelligent avec des seuils variables sur la base des lectures de vibration

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2618774C1 (ru) * 2016-01-11 2017-05-11 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Способ контроля вибрационного горения в камере сгорания газотурбинного двигателя
DE102019204422A1 (de) 2019-03-29 2020-10-01 Siemens Aktiengesellschaft Vorhersage einer Verbrennungsdynamik einer Gasturbine

Citations (3)

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Publication number Priority date Publication date Assignee Title
JPS6341727A (ja) * 1986-08-05 1988-02-23 Babcock Hitachi Kk 燃焼振動監視装置
EP1327824A1 (fr) * 2001-12-24 2003-07-16 ABB Schweiz AG Détection et réglage du point de fonctionnement d'une chambre de combustion de turbine à gaz en approchant la limite d'extinction
EP1688671A1 (fr) * 2005-02-03 2006-08-09 ALSTOM Technology Ltd Méthode de protection et système de contrôle pour turbine à gaz

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JPS55110823A (en) * 1979-02-16 1980-08-26 Kobe Steel Ltd Controlling method of air ratio at combustion furnace
RU2046312C1 (ru) * 1991-10-08 1995-10-20 Машиностроительное конструкторское бюро "Гранит" Способ диагностирования степени засорения коллектора с форсунками камеры сгорания газотурбинного двигателя
US5719791A (en) * 1995-03-17 1998-02-17 Georgia Tech Research Corporation Methods, apparatus and systems for real time identification and control of modes of oscillation
US5706643A (en) * 1995-11-14 1998-01-13 United Technologies Corporation Active gas turbine combustion control to minimize nitrous oxide emissions
US5865609A (en) * 1996-12-20 1999-02-02 United Technologies Corporation Method of combustion with low acoustics
GB2344883B (en) * 1998-12-16 2003-10-29 Graviner Ltd Kidde Flame monitoring methods and apparatus

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6341727A (ja) * 1986-08-05 1988-02-23 Babcock Hitachi Kk 燃焼振動監視装置
EP1327824A1 (fr) * 2001-12-24 2003-07-16 ABB Schweiz AG Détection et réglage du point de fonctionnement d'une chambre de combustion de turbine à gaz en approchant la limite d'extinction
EP1688671A1 (fr) * 2005-02-03 2006-08-09 ALSTOM Technology Ltd Méthode de protection et système de contrôle pour turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520863A1 (fr) * 2011-05-05 2012-11-07 Alstom Technology Ltd Procédé de protection d'un moteur à turbine à gaz contre des valeurs de processus dynamique élevées et moteur de turbine à gaz pour l'exécution de ce procédé
US9068512B2 (en) 2011-05-05 2015-06-30 Alstom Technology Ltd. Method for protecting a gas turbine engine against high dynamical process values and gas turbine engine for conducting the method
EP3045676A1 (fr) 2015-01-13 2016-07-20 Siemens Aktiengesellschaft Procédé destiné à éviter un détachement de courant rotatif
EP3101343A1 (fr) * 2015-06-05 2016-12-07 Siemens Aktiengesellschaft Procede de commande intelligent avec des seuils variables sur la base des lectures de vibration
WO2016193069A1 (fr) * 2015-06-05 2016-12-08 Siemens Aktiengesellschaft Procédé de commande intelligent avec seuils variables sur la base de lectures de vibration

Also Published As

Publication number Publication date
EP2417395A2 (fr) 2012-02-15
ES2700444T3 (es) 2019-02-15
CN102713438A (zh) 2012-10-03
RU2011145037A (ru) 2013-05-20
RU2548233C2 (ru) 2015-04-20
WO2010115921A2 (fr) 2010-10-14
EP2417395B1 (fr) 2018-09-05
CN102713438B (zh) 2014-09-10
WO2010115921A3 (fr) 2013-03-14

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