EP2151629A2 - Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz - Google Patents

Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz Download PDF

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Publication number
EP2151629A2
EP2151629A2 EP09167518A EP09167518A EP2151629A2 EP 2151629 A2 EP2151629 A2 EP 2151629A2 EP 09167518 A EP09167518 A EP 09167518A EP 09167518 A EP09167518 A EP 09167518A EP 2151629 A2 EP2151629 A2 EP 2151629A2
Authority
EP
European Patent Office
Prior art keywords
burners
pxi
remaining
premix
seats
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.)
Granted
Application number
EP09167518A
Other languages
German (de)
English (en)
Other versions
EP2151629B1 (fr
EP2151629A8 (fr
EP2151629A3 (fr
Inventor
Federico Bonzani
Lorena Della Fiore
Carlo Piana
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP2151629A2 publication Critical patent/EP2151629A2/fr
Publication of EP2151629A8 publication Critical patent/EP2151629A8/fr
Publication of EP2151629A3 publication Critical patent/EP2151629A3/fr
Application granted granted Critical
Publication of EP2151629B1 publication Critical patent/EP2151629B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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 a method for determining the location of burners in an annular combustion chamber of a gas turbine.
  • Said technology substantially envisages having an annular combustion chamber comprising a plurality of burner assemblies set at the same distance apart from one another, each of which comprises a premix burner, also referred to as primary burner, and a pilot burner, also referred to as secondary burner.
  • the premix burner is supplied with an air-fuel mixture, with marked excess of air, for the purpose of generating a flame such as to guarantee a uniform temperature range and avoid possible temperature peaks that may lead to high emissions of NO x at the exhaust.
  • the pilot burner is instead supplied with fuel and stabilizes the flame generated by the premix burner.
  • thermo-acoustic instability which are determined by the fluctuation of the parameters of the fluids present in the combustion chamber.
  • Combustion chambers are known that have a system of injection differentiated for each premix burner and/or pilot burner for reducing the phenomena of thermo-acoustic instability. Also known are combustion chambers having flow deflectors designed to deflect the flow at output from the premix burner in such a way as to reduce the phenomena of thermo-acoustic instability.
  • An aim of the present invention is to provide a method for determining the location of burners of an annular combustion chamber of a gas turbine that will be able to overcome the drawbacks of the known art highlighted herein; in particular, an aim of the invention is to provide a method for determining the location of the burners of an annular combustion chamber of a gas turbine that will be able to minimize the phenomena of thermo-acoustic instability.
  • the present invention regards a method for determining the location of burners in an annular combustion chamber of a gas turbine comprising the steps of:
  • Designated by the reference number 1 in Figure 1 is an annular combustion chamber for a gas turbine (not illustrated for reasons of simplicity in the attached figures).
  • the combustion chamber 1 extends along a longitudinal axis A and comprises a plurality of seats 2, each of which is designed to be engaged by a burner assembly 3 ( Figure 2 ).
  • the seats 2 are arranged along a circular path in the proximity of a peripheral edge 5 of the combustion chamber 1.
  • the seats 2 and the burner assemblies 3 are twenty-four.
  • each burner assembly 3 extends along an axis B and comprises a pilot burner 6 set along the axis B and supplied with fuel, and a premix burner 7 set substantially around the pilot burner 6 and supplied with an air-fuel mixture.
  • the premix burner 7 can be of the type provided with a cylindrical outlet element 9, commonly referred to as “cylindrical burner outlet” (and hereinafter referred to as "CBO element") or else of the type without said CBO element 9.
  • the CBO element 9 is substantially a prolongation of the outlet channel of the premix burner 7 and is designed to stabilize the flame generated by the premix burner 7.
  • the location of the premix burners 7 and of the pilot burners 6 in the seats 2 of the combustion chamber 1 is made in accordance with the method according to the present invention.
  • the method envisages determining the location of the premix burners 7 and subsequently determining the location of the pilot burners 6 in the combustion chamber 1.
  • the method according to the present invention envisages:
  • the step of associating a seat 2 of the combustion chamber 1 to each premix burner 7 comprises the steps of:
  • the method according to the present invention envisages:
  • the step of associating a seat 2 of the combustion chamber 1 to each pilot burner 6 comprises the steps of:
  • each pilot burner 6 and each premix burner 7 is connected to a device (not illustrated) comprising an air-supply circuit, in which pressurized air flows, connected to the inlet of the gas line of the burner under test via a purposely provided pipe, and a computer.
  • the flow rate is acquired continuously through a flow-meter set in a section of the air-supply circuit substantially at the inlet of the burner under test. If the value of the flow rate acquired remains constant for approximately thirty seconds, the value of the flow rate is stored by the computer.
  • the value of flow rate is calculated in such a way as to render the tests independent of variations of pressure and/or temperature.
  • the supply circuit is supplied with air at a supply pressure p such that the ratio between the supply pressure p and the atmospheric pressure p a expressed in mbar, is:
  • the flow rate detected is appropriately normalized with respect to the ambient temperature (measured in degrees Kelvin) and consequently is measured in m 3 /s ⁇ K 1/2 .
  • the method according to the present invention presents the following advantages.
  • the application of the method according to the present invention determines a reduction of the thermo-acoustic instability of the combustion chamber 1.
  • the method according to the present invention determines both for the premix burners 7 and for the pilot burners 6 the best configuration for generating a temperature range that limits the propagation of the thermo-acoustic waves generated by the phenomenon of humming previously described. Furthermore, the uniformity of evolution between the flow rates Q PXi of the premix burners and the flow rates Q Pi of the pilot burners enables maximum limitation of the NOx emissions produced at exhaust.
  • the method according to the present invention is based exclusively upon the measurement of the effective flow rates Q PXi and Q Pi , i.e., affected by the machining tolerances, of the premix burners 7 and pilot burners 6, preventing any need to intervene with mechanical modifications on the premix burners 7 and/or pilot burners 6 and without intervening on the control device of the combustion chamber 1.
  • a further advantage is represented by the possibility of using premix burners 7 and pilot burners 6 having a deviation ⁇ Q PXi , ⁇ Q Pi that is substantially wide (up to 5%), which otherwise would have to be rejected in so far as not compliant with the specifications normally considered in the known art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Volume Flow (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Feeding And Controlling Fuel (AREA)
EP20090167518 2008-08-08 2009-08-07 Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz Active EP2151629B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITMI2008A001514A IT1391245B1 (it) 2008-08-08 2008-08-08 Metodo per determinare la collocazione di bruciatori in una camera di combustione anulare di una turbina a gas

Publications (4)

Publication Number Publication Date
EP2151629A2 true EP2151629A2 (fr) 2010-02-10
EP2151629A8 EP2151629A8 (fr) 2010-05-26
EP2151629A3 EP2151629A3 (fr) 2013-06-26
EP2151629B1 EP2151629B1 (fr) 2014-07-23

Family

ID=40528252

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20090167518 Active EP2151629B1 (fr) 2008-08-08 2009-08-07 Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz

Country Status (2)

Country Link
EP (1) EP2151629B1 (fr)
IT (1) IT1391245B1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5983643A (en) * 1996-04-22 1999-11-16 Asea Brown Boveri Ag Burner arrangement with interference burners for preventing pressure pulsations
US6430930B1 (en) * 1998-08-11 2002-08-13 Abb Ab Arrangement for reduction of acoustic vibrations in a combustion chamber
US20020134086A1 (en) * 2001-02-22 2002-09-26 Klaus Doebbeling Process for the operation of an annular combustion chamber, and annular combustion chamber
WO2004109188A1 (fr) * 2003-06-05 2004-12-16 Alstom Technology Ltd Procede permettant de faire fonctionner un dispositif bruleur annulaire dans un etage de rechauffement intermediaire d'un dispositif de combustion a plusieurs etages d'une turbine a gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5983643A (en) * 1996-04-22 1999-11-16 Asea Brown Boveri Ag Burner arrangement with interference burners for preventing pressure pulsations
US6430930B1 (en) * 1998-08-11 2002-08-13 Abb Ab Arrangement for reduction of acoustic vibrations in a combustion chamber
US20020134086A1 (en) * 2001-02-22 2002-09-26 Klaus Doebbeling Process for the operation of an annular combustion chamber, and annular combustion chamber
WO2004109188A1 (fr) * 2003-06-05 2004-12-16 Alstom Technology Ltd Procede permettant de faire fonctionner un dispositif bruleur annulaire dans un etage de rechauffement intermediaire d'un dispositif de combustion a plusieurs etages d'une turbine a gaz

Also Published As

Publication number Publication date
ITMI20081514A1 (it) 2010-02-09
EP2151629B1 (fr) 2014-07-23
EP2151629A8 (fr) 2010-05-26
IT1391245B1 (it) 2011-12-01
EP2151629A3 (fr) 2013-06-26

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