EP2848865A1 - Procédé de stabilisation thermoacoustique - Google Patents

Procédé de stabilisation thermoacoustique Download PDF

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Publication number
EP2848865A1
EP2848865A1 EP13184151.2A EP13184151A EP2848865A1 EP 2848865 A1 EP2848865 A1 EP 2848865A1 EP 13184151 A EP13184151 A EP 13184151A EP 2848865 A1 EP2848865 A1 EP 2848865A1
Authority
EP
European Patent Office
Prior art keywords
burners
burner
oxidant
fuel
mass flow
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Withdrawn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
EP13184151.2A
Other languages
German (de)
English (en)
Inventor
Franklin Marie Genin
Naresh Aluri
Bruno Schuermans
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP13184151.2A priority Critical patent/EP2848865A1/fr
Publication of EP2848865A1 publication Critical patent/EP2848865A1/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Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to gas turbine combustion systems. It refers to a thermoacoustic stabilization method, which keeps engine pulsations under control for the lifetime of the engine.
  • premix burners for example EV burners (EV stands for environmental) as described in general in EP 0 321 809 B1 or US 4,932,861 are used.
  • EV burners EV stands for environmental
  • the flame stabilization that is necessary by using lean fuel relying mostly on free standing recirculation regions. These flames are typically very sensitive to flow perturbations and easily couple with the dynamics of the combustion chamber to lead to thermoacoustic instabilities. These flow dynamics have a strong impact on the combustion quality, components lifetime, etc., and are thus undesirable.
  • thermoacoustic stabilization currently used in gas turbines rely on passive control, and use either fuel staging in burner groups (operation concepts where groups of burners are defined to operate at different power through fuel staging), burner staging (burners with multiple fuel nozzles to combine the stability brought by rich zones to leaner flame regions) or Helmholtz resonators/dampers.
  • thermoacoustic stabilization for gas turbine combustion systems composed of multiple burners which overcomes the disadvantages of the prior art methods.
  • thermoacoustic stabilization of gas turbine combustors with multiple burners wherein the burners are arranged in at least one burner group and each of them is supplied with fuel and oxidant, is characterized in operating neighboring burners in that burner group at different nominal velocities of the oxidant by an oxidant pressure drop across the individual burners. This is called in the following "velocity staging".
  • the nominal burner velocity is proportional to the mass flow of oxidant through the burner.
  • the core of the invention is to operate neighboring burners of gas turbine combustors at different nominal mass flows of oxidant by an oxidant pressure drop across the individual burners.
  • the oxidant is for example air or air with water addition etc.
  • thermoacoustic stabilization at minimal implementation costs. Furthermore, it can be retrofitted.
  • an added value is to modulate the specific powers of the individual burners in relation with their nominal velocities (velocity and fuel staging), keeping the temperature spread across burners to a low value and hence reducing NOx penalty.
  • the stabilization is as effective as the state of the art approaches but without the undesired increasing of NOx that is associated with the known prior art methods.
  • a quantification of the response of individual burners to acoustic perturbations can be made through measurements of flame transfer functions (FTF hereafter).
  • FTF flame transfer functions
  • the pressure drop right upstream of the burner can be controlled on a burner by burner basis, by implementing varying sieves upstream of the burners.
  • the oxidant mass flow will be redistributed across burners, providing more oxidant flow to the burner with low pressure drop (higher burner velocity) and less oxidant flow to the burners with an additional pressure drop induced by the sieve.
  • This arrangement leads to a burner velocity staging which provides additional stability to the system.
  • orifices are implemented in the fuel distribution of the burner groups to control the fuel mass flows according to the respective burner oxidant mass flow and approach homogeneous flame temperature operation of the different groups.
  • the present velocity staging concept is illustrated here for a specific annular combustor with a predefined burner grouping. It is clear, however, that a similar velocity staging can be achieved in all other gas turbines types where multiple burners are used, in annular, cannular or silo combustors.
  • Fig. 1 shows a schematic view of an annular combustor 1 of the front segments 360° (front plate 4), with 24 premix burners 2 of the EV type (double-cone type).
  • the burners 2 are arranged in 8 groups 3, each of four burners 2.
  • One group 3 is circled with a dotted line in Fig. 1 .
  • the following figures focus on such a group of burners.
  • Fig. 2 shows in a schematic view such an EV burner 2 from Fig.1 in the longitudinal direction of the burner for explanation of the nomenclature and should always be discussed in connection with the following figures.
  • the burner 2 opens in the front plate 4.
  • Fuel 5 and oxidant 6 are supplied to the burner 2.
  • a longer fuel line 5 means more fuel mass flow and a thicker oxidant line 6 means more oxidant flow.
  • the burner is surrounded with a sieve 7, the thickness of the dashed line indicates the blockage strength.
  • Reference number 8 indicates the flame front.
  • Fig. 3 shows a schematic view of a burner group 3 with four burners 2 according to Fig. 1 (Prior Art).
  • Fig. 4 shows a second schematic view of a burner group 3 with four burners 4 according to Fig. 1 (Prior Art).
  • a pulsation mitigation according to the known prior art is here achieved wherein the fuel only is staged (unequally fuel distribution-the burner 2 below in Fig. 4 has a lower fuel mass flow (M_fuel ⁇ m_fuel_avg) than the other three burners (M_fuel>m_fuel_avg)), and all burners 2 get same amount of oxidant 6 as indicated by the arrows 6 with the same thickness.
  • M_fuel ⁇ m_fuel_avg fuel mass flow
  • M_fuel>m_fuel_avg average flame temperature
  • a higher amount of oxidant 6 (higher mass flow) is supplied to one burner 2 (see burner 2 below in Fig. 5 ) while the other three burners 2 are each supplied with a lower amount of oxidant 6 as can be seen by the thinner lines in Fig. 5 .
  • a lower amount of oxidant 6 is supplied to one burner 2 (see burner 2 below in Fig. 6 with a lower mass flow of oxidant 6) while the other three burners 2 are each supplied with a higher amount of oxidant 6 as can be seen by the thicker lines in Fig. 6 .
  • thermoacoustic stabilization method The application in velocity staging in combination with uniform fuel injection is a thermoacoustic stabilization method, but leads also to flame temperature staging which should be avoided because of the NOx penalty.
  • Fig. 7 shows the preferred embodiment of the present invention in a schematic view of a burner group 3 according to Fig. 1 with both velocity and fuel staging.
  • a lower amount of oxidant 6 is supplied to one burner 2 (see burner 2 below in Fig. 7 ) while the other three burners 2 are each supplied with a higher amount of oxidant 6 as can be seen by the thicker lines in Fig. 7 .
  • thermoacoustic pulsations mitigations whereby a velocity staging between burners is applied. Such an approach permits neighboring burners to be detuned hence increasing the stability. Combining this to a fuel distribution that matches the oxidant distribution, the combustor can be operated near homogeneous conditions, so that the penalty in pollutant emissions is reduced to its minimum.
  • This approach can be implemented in a number of different ways, for example installation of different burner sizes, of burners with different pressure drop characteristics, etc.
  • all burners are identical, and the individual burners pressure drops are controlled by the implementation of different sieves (already implemented in the engines, however currently with same characteristics for all burners) upstream of the burners.
  • This approach leads to velocity staging with minimal cost because such sieves are inexpensive.
  • the proposed staging concept is applicable to any gas turbine system composed of multiple burners (annular, cannular, silo).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP13184151.2A 2013-09-12 2013-09-12 Procédé de stabilisation thermoacoustique Withdrawn EP2848865A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13184151.2A EP2848865A1 (fr) 2013-09-12 2013-09-12 Procédé de stabilisation thermoacoustique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13184151.2A EP2848865A1 (fr) 2013-09-12 2013-09-12 Procédé de stabilisation thermoacoustique

Publications (1)

Publication Number Publication Date
EP2848865A1 true EP2848865A1 (fr) 2015-03-18

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EP13184151.2A Withdrawn EP2848865A1 (fr) 2013-09-12 2013-09-12 Procédé de stabilisation thermoacoustique

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EP (1) EP2848865A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4148327A1 (fr) * 2021-09-09 2023-03-15 Ansaldo Energia Switzerland AG Moteur à turbine à gaz à stabilisation de mode acoustique, procédé de commande et procédé de modification de moteur à turbine à gaz

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4932861A (en) 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
WO1998011383A2 (fr) * 1996-09-09 1998-03-19 Siemens Aktiengesellschaft Dispositif et procede pour la combustion d'un combustible dans l'air
WO1998012478A1 (fr) * 1996-09-16 1998-03-26 Siemens Aktiengesellschaft Procede et dispositif pour la combustion d'un combustible avec de l'air
GB2375601A (en) * 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
EP1158247B1 (fr) 2000-05-26 2006-04-19 ALSTOM Technology Ltd Dispositif pour la réduction des vibrations accoustiques dans une chambre de combustion
WO2006082210A1 (fr) * 2005-02-04 2006-08-10 Enel Produzione S.P.A. Reduction d’oscillation thermoacoustique dans des chambres de combustion de turbine a gaz avec plenum annulaire
EP1906093A2 (fr) * 2006-09-26 2008-04-02 United Technologies Corporation Procédé pour le contrôle d'instabilités thermoacoustiques dans une chambre de combustion
WO2010115980A2 (fr) 2009-04-11 2010-10-14 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz
US8205714B2 (en) 2008-08-14 2012-06-26 Alstom Technology Ltd. Method for adjusting a Helmholtz resonator and an adjustable Helmholtz resonator

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4932861A (en) 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
WO1998011383A2 (fr) * 1996-09-09 1998-03-19 Siemens Aktiengesellschaft Dispositif et procede pour la combustion d'un combustible dans l'air
WO1998012478A1 (fr) * 1996-09-16 1998-03-26 Siemens Aktiengesellschaft Procede et dispositif pour la combustion d'un combustible avec de l'air
EP1158247B1 (fr) 2000-05-26 2006-04-19 ALSTOM Technology Ltd Dispositif pour la réduction des vibrations accoustiques dans une chambre de combustion
GB2375601A (en) * 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
WO2006082210A1 (fr) * 2005-02-04 2006-08-10 Enel Produzione S.P.A. Reduction d’oscillation thermoacoustique dans des chambres de combustion de turbine a gaz avec plenum annulaire
EP1906093A2 (fr) * 2006-09-26 2008-04-02 United Technologies Corporation Procédé pour le contrôle d'instabilités thermoacoustiques dans une chambre de combustion
US8205714B2 (en) 2008-08-14 2012-06-26 Alstom Technology Ltd. Method for adjusting a Helmholtz resonator and an adjustable Helmholtz resonator
WO2010115980A2 (fr) 2009-04-11 2010-10-14 Alstom Technology Ltd. Chambre de combustion dotée d'un amortisseur de helmholtz

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4148327A1 (fr) * 2021-09-09 2023-03-15 Ansaldo Energia Switzerland AG Moteur à turbine à gaz à stabilisation de mode acoustique, procédé de commande et procédé de modification de moteur à turbine à gaz

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