EP3045676A1 - Procédé destiné à éviter un détachement de courant rotatif - Google Patents
Procédé destiné à éviter un détachement de courant rotatif Download PDFInfo
- Publication number
- EP3045676A1 EP3045676A1 EP15150919.7A EP15150919A EP3045676A1 EP 3045676 A1 EP3045676 A1 EP 3045676A1 EP 15150919 A EP15150919 A EP 15150919A EP 3045676 A1 EP3045676 A1 EP 3045676A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- compressor
- detecting
- rotating stall
- gas turbine
- detected
- 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- Withdrawn
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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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
- F05D2270/101—Compressor surge or stall
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
Definitions
- the invention relates to a method for preventing a rotating stall in an operating state of a compressor for a gas turbine. It further relates to a compressor for a gas turbine.
- a gas turbine is a turbomachine in which a hot and compressed gas is expanded, converting thermal energy into mechanical energy.
- the hot gas is produced by combustion of a gaseous or liquid fuel in a combustion chamber, which is further supplied with compressed air from an upstream compressor.
- the energy obtained is used for example in power plants to drive a generator, wherein a part of the energy is provided in the gas turbine for driving the compressor.
- the invention is based on the consideration that a more reliable operation of the compressor and the gas turbine could be achieved in that the "rotating stall" is detected early. It was recognized that this can be detected by striking changes in the frequency spectrum of vibrations in the area of the compressor. Therefore, via a corresponding pattern recognition of the incipient rotating stall can be detected and reduced by introducing appropriate countermeasures. An emergency shutdown of the gas turbine is avoided.
- the above-mentioned operating state in which the "rotating stall" is to be prevented is in an advantageous embodiment of the method, the startup of the compressor.
- the startup of the compressor In particular, during the starting process of the compressor and the gas turbine, it is necessary that a sufficient air mass flow is available in the combustion chamber and in the turbine. The occurrence of a "rotating stall” would lead here to a termination of the startup process, which can be avoided by the described method.
- the measured vibration quantity used to detect the "rotating stall" is advantageously an alternating pressure in the area of the compressor.
- the area of the compressor in which this oscillation variable and in particular the alternating pressure is detected is advantageously a compressor discharge.
- Such compressor extracts are used to remove compressed air at different pressure levels, which then z. B. is used for cooling.
- the object is therefore also achieved by the compressor comprises a change-pressure measuring device in a compressor extraction.
- the at least one alternating pressure at the burner flange, with which the alternating pressure in the combustion chamber region is measured, as well as the detection of the at least one combustion chamber acceleration on the housing provide further measurement data which are used to improve the Detection of a starting "rotating stall" can be used.
- the detection of the vibration magnitude further advantageously comprises detecting a plurality of frequency bands, i. H. the detected vibration magnitude is z. B. split by means of a Fourier decomposition into their frequency components and analyzed in the frequency domain by means of the aforementioned pattern recognition.
- the frequency bands are detected by 40 Hz and / or 60 Hz and / or 80 Hz, in particular during the starting process advantageously, d. H. Frequency bands in which the frequencies mentioned are located.
- the excitation frequencies 1300 to 4500 Hz can be observed.
- the excitation frequencies are given by the number of blades multiplied by the speed.
- the respective frequency band advantageously has a width of 10 Hz, ie. H.
- a frequency band analysis is carried out at 40, 60 and 80 Hz, each in a band of +/- 5 Hz.
- the reduction of a fuel quantity in the combustion chamber of the gas turbine downstream of the compressor is also initiated as a countermeasure.
- a blow-off flap ie a device for blowing compressor air introduced before entering the combustion chamber.
- a compressor for a gas turbine advantageously comprises a control device designed to carry out the described method.
- a gas turbine advantageously comprises a compressor described here.
- the advantages achieved by the invention are, in particular, that the early detection of the "rotating stall" by means of vibration analysis in particular of the alternating pressure in the compressor, a termination of a gas turbine start can be prevented.
- the optimized operation avoids strong alternating pressures and accelerations that could otherwise damage the gas turbine and its compressor.
- FIG. 1 shows a gas turbine 100 in a longitudinal partial section.
- a gas turbine 100 is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
- the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
- a rotation axis 102 axial direction
- rotor 103 which is also referred to as a turbine runner.
- an intake housing 104 a compressor 105, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
- the annular combustion chamber 106 communicates with an annular hot gas channel 111.
- Each turbine stage 112 is formed from two blade rings.
- a row 125 of blades 120 is formed in the hot gas channel 111 of a row of guide vanes 115.
- the blades 120, 130 are profiled in a slightly curved manner, similar to an aircraft wing.
- the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133.
- the rotor blades 120 thus form components of the rotor or rotor 103.
- Coupled to the rotor 103 is a generator or a working machine (not shown).
- air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
- the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
- the mixture is then burned to form the working fluid 113 in the combustion chamber 110. From there, the working fluid 113 flows along the hot gas passage 111 past the vanes 130 and the blades 120.
- the fluid flow is withdrawn by the vortex-free as possible laminar flow around the turbine blades 120, 130, a portion of its internal energy, which is applied to the blades 120 of the Turbine 108 passes. About this then the rotor 103 is rotated, whereby initially the compressor 105 is driven. The usable power is delivered to the work machine, not shown.
- the compressor 105 has a number of non-illustrated compressed air extractions. These are arranged in different stages of the compressor 105, so that compressed air can be taken at different pressure levels. This is then z. B. used for cooling in the turbine 108.
- gas turbine 100 is designed to avoid a rotating stall ("rotating stall") in particular during the starting process.
- the gas turbine 100 has a device for dynamic alternating pressure measurement on the flange of the burner 107, a device for measuring the acceleration of the combustion chamber 106 on the housing 138 and a device for dynamic alternating pressure measurement in the withdrawals of the compressor 105 arranged (all not shown). Their signals are forwarded to a likewise not shown control device of the gas turbine 100, which is designed to carry out the method described below.
- FIG. 2 2 shows a schematic flow diagram of the method 200 for avoiding a rotating stall in the compressor 105.
- the method 200 is performed permanently or alternatively cyclically.
- step 202 a detection of the dynamic alternating pressure at the flange of one of the burners 107 with the described device takes place.
- step 204 a detection of the acceleration of the combustion chamber 106 on the housing 138 with the described device takes place in step 204.
- step 206 a detection of the dynamic alternating pressure in the withdrawals of the compressor 105 with the described devices.
- step 208 the detected quantities are subjected to a frequency analysis. Frequency bands of 35 to 45 Hz, 55 to 65 Hz and 75 to 85 Hz are formed of each size.
- step 210 pattern recognition is performed in the mentioned frequency bands. Here, conspicuous changes are searched, which point to an incipient "rotating stall”. As soon as a starting "rotating stall" is detected in step 210, several countermeasures are triggered in steps 212, 214 and 216 in parallel.
- step 212 the closing of a compressor pilot vane of the compressor 105, i. H. an inlet side vane in the compressor 105.
- step 214 the amount of fuel to the burners 107 is reduced.
- step 216 a Abblaseklappe not shown, opened by the air from the compressor 105 can escape.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15150919.7A EP3045676A1 (fr) | 2015-01-13 | 2015-01-13 | Procédé destiné à éviter un détachement de courant rotatif |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15150919.7A EP3045676A1 (fr) | 2015-01-13 | 2015-01-13 | Procédé destiné à éviter un détachement de courant rotatif |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3045676A1 true EP3045676A1 (fr) | 2016-07-20 |
Family
ID=52339045
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15150919.7A Withdrawn EP3045676A1 (fr) | 2015-01-13 | 2015-01-13 | Procédé destiné à éviter un détachement de courant rotatif |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP3045676A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111622843A (zh) * | 2019-02-28 | 2020-09-04 | 三菱日立电力系统株式会社 | 燃气轮机的运行方法以及燃气轮机 |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4196472A (en) * | 1977-09-09 | 1980-04-01 | Calspan Corporation | Stall control apparatus for axial flow compressors |
US4380893A (en) * | 1981-02-19 | 1983-04-26 | The Garrett Corporation | Compressor bleed air control apparatus and method |
US4449358A (en) * | 1981-07-24 | 1984-05-22 | General Electric Company | Method and apparatus for promoting a surge condition in a gas turbine |
US5915917A (en) * | 1994-12-14 | 1999-06-29 | United Technologies Corporation | Compressor stall and surge control using airflow asymmetry measurement |
EP1256726A1 (fr) * | 2001-04-17 | 2002-11-13 | General Electric Company | Procédé et appareil de prediction continu, de surveillance et contrôle de stabilité d'un compresseur via détection des précurseurs de décollement tournat et du pompage |
US20040037693A1 (en) * | 2002-08-23 | 2004-02-26 | York International Corporation | System and method for detecting rotating stall in a centrifugal compressor |
US20040159103A1 (en) * | 2003-02-14 | 2004-08-19 | Kurtz Anthony D. | System for detecting and compensating for aerodynamic instabilities in turbo-jet engines |
DE102004052433A1 (de) | 2003-10-30 | 2005-07-07 | Mitsubishi Heavy Industries, Ltd. | Gasturbinen-Steuer- bzw. Regelungsvorrichtung, Gasturbinensystem und Gasturbinensteuer- bzw. Regelungsverfahren |
EP2239505A1 (fr) | 2009-04-08 | 2010-10-13 | Siemens Aktiengesellschaft | 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 |
EP2410154A2 (fr) * | 2010-07-22 | 2012-01-25 | General Electric Company | Procédé de démarrage de turbines à gas et dispositif de réglage |
FR2972492A1 (fr) * | 2011-03-08 | 2012-09-14 | Snecma | Turbomachine comportant une vanne anti-pompage |
EP2626569A1 (fr) * | 2012-02-09 | 2013-08-14 | Siemens Aktiengesellschaft | Procédé destiné à éviter les chocs de pompes dans un compresseur |
-
2015
- 2015-01-13 EP EP15150919.7A patent/EP3045676A1/fr not_active Withdrawn
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4196472A (en) * | 1977-09-09 | 1980-04-01 | Calspan Corporation | Stall control apparatus for axial flow compressors |
US4380893A (en) * | 1981-02-19 | 1983-04-26 | The Garrett Corporation | Compressor bleed air control apparatus and method |
US4449358A (en) * | 1981-07-24 | 1984-05-22 | General Electric Company | Method and apparatus for promoting a surge condition in a gas turbine |
US5915917A (en) * | 1994-12-14 | 1999-06-29 | United Technologies Corporation | Compressor stall and surge control using airflow asymmetry measurement |
EP1256726A1 (fr) * | 2001-04-17 | 2002-11-13 | General Electric Company | Procédé et appareil de prediction continu, de surveillance et contrôle de stabilité d'un compresseur via détection des précurseurs de décollement tournat et du pompage |
US20040037693A1 (en) * | 2002-08-23 | 2004-02-26 | York International Corporation | System and method for detecting rotating stall in a centrifugal compressor |
US20040159103A1 (en) * | 2003-02-14 | 2004-08-19 | Kurtz Anthony D. | System for detecting and compensating for aerodynamic instabilities in turbo-jet engines |
DE102004052433A1 (de) | 2003-10-30 | 2005-07-07 | Mitsubishi Heavy Industries, Ltd. | Gasturbinen-Steuer- bzw. Regelungsvorrichtung, Gasturbinensystem und Gasturbinensteuer- bzw. Regelungsverfahren |
EP2239505A1 (fr) | 2009-04-08 | 2010-10-13 | Siemens Aktiengesellschaft | 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 |
EP2410154A2 (fr) * | 2010-07-22 | 2012-01-25 | General Electric Company | Procédé de démarrage de turbines à gas et dispositif de réglage |
FR2972492A1 (fr) * | 2011-03-08 | 2012-09-14 | Snecma | Turbomachine comportant une vanne anti-pompage |
EP2626569A1 (fr) * | 2012-02-09 | 2013-08-14 | Siemens Aktiengesellschaft | Procédé destiné à éviter les chocs de pompes dans un compresseur |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111622843A (zh) * | 2019-02-28 | 2020-09-04 | 三菱日立电力系统株式会社 | 燃气轮机的运行方法以及燃气轮机 |
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RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SIEMENS AKTIENGESELLSCHAFT |
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Effective date: 20170721 |