EP1557607A1 - Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant - Google Patents

Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant Download PDF

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Publication number
EP1557607A1
EP1557607A1 EP04001242A EP04001242A EP1557607A1 EP 1557607 A1 EP1557607 A1 EP 1557607A1 EP 04001242 A EP04001242 A EP 04001242A EP 04001242 A EP04001242 A EP 04001242A EP 1557607 A1 EP1557607 A1 EP 1557607A1
Authority
EP
European Patent Office
Prior art keywords
burner
cooling air
component
pressure
outlet
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
EP04001242A
Other languages
German (de)
English (en)
Other versions
EP1557607B1 (fr
Inventor
Dietmar Dr. Granser
Jens Kleinfeld
Hans Maghon
Holger Dr. Streb
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 AT04001242T priority Critical patent/ATE483138T1/de
Priority to EP04001242A priority patent/EP1557607B1/fr
Priority to DE502004011695T priority patent/DE502004011695D1/de
Publication of EP1557607A1 publication Critical patent/EP1557607A1/fr
Application granted granted Critical
Publication of EP1557607B1 publication Critical patent/EP1557607B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the invention relates to a method for cooling a component a gas turbine with a combustion chamber upstream Burner outlet of a burner, wherein the component via a cooling air flow from an input side with cooling air is charged.
  • the invention further relates to a burner with a component to be cooled, one of a combustion chamber a gas turbine upstream burner outlet of the burner and one of the component from an input side with cooling air acting cooling air flow.
  • a gas turbine is an engine that generates heat energy converts a hot gas into mechanical energy and it is for example as a drive unit, preferably used to generate electricity.
  • the gas turbine has different components. In a compressor sucked in air is compressed. The compressed Air flows through a burner located behind the compressor to. There it is mixed with injected fuel and in burned the subsequent combustion chamber. As fuel can serve natural gas or fuel oil.
  • the combustion chamber has a Combustion chamber in which the combustion takes place.
  • the combustion chamber upstream are a number of burners, with each one Burner one burner outlet in the form of a flow channel is located directly where the fuel injection and air supply takes place immediately.
  • the compressed Air is converted to hot gas by combustion of the fuel with a temperature that is above in modern machines of 1400 ° C.
  • the number of burners can thereby advantageously the combustion chamber can be arranged around.
  • the combustion chamber can be arranged around.
  • it is in the arrangement around a concentric around the combustion chamber arranged around annular burner assembly.
  • a gas turbine is expediently designed such that it delivers as high a power as possible or has the highest possible efficiency, the efficiency being the ratio between the power delivered and the power supplied.
  • the efficiency being the ratio between the power delivered and the power supplied.
  • it is important that a combustion-resulting NO x emission and the emission of other harmful combustion gases should be kept as low as possible.
  • the heated components of the Gas turbine in particular such components of the gas turbine, the Have hot gas contact, especially the components of a combustion chamber, be cooled with cooling air. So far, it's common to remove the cooling air from the compressor and to cool it Component via a cooling air duct from an input side to apply the cooling air, d. H. the cooling air the Supply component and then inflate this with cooling air.
  • Desirable would be a concept for cooling a component of a Gas turbine, with a comparable good efficiency contributes to the reduction of pollutant emissions.
  • the invention begins, whose task it is to provide a method for cooling a component of a gas turbine and a device with a component to be cooled in which the cooling concept is designed in such a way that that the efficiency of the gas turbine is not reduced and the Pollutant emission of the gas turbine is lowered.
  • the invention is based on the consideration that so far in the Framework of the open cooling air concept pursued solution principle unfavorable with regard to the pollutant emission of the gas turbine is.
  • the invention has now recognized that it is particularly advantageous in terms of Pollutant emission proves the cooling air in a closed Cooling air concept, if possible, to the burner, d. H. in particular to supply the burner flow.
  • the following will be the cooling air already supplied to the burner outlet and not first the combustion chamber of the combustion chamber. That's the way it will be now allows the cooling air completely at the mixing with fuel in the burner and burning in the burner downstream combustion chamber can participate.
  • the improved mixing of the cooling air according to the present concept reduces the overall fuel-air ratio. This measure reduces from the outset the combustion temperature to an advantageous level and as a result of the formation of NO x .
  • the closed cooling air concept thus contributes to a significant reduction in NO x emissions. Emission of CO and other unburned hydrocarbons is still kept low.
  • the proposed here supply of cooling air to the burner outlet in the context of the closed cooling concept is in the Frame of the invention in a particularly effective manner thereby achieved that when operating the burner from the input side or the burner inlet to the burner outlet or the Combustion chamber towards a pressure gradient in the cooling air flow or is maintained in the burner flow channel.
  • the cooling air becomes the burner outlet by taking advantage of this pressure gradient fed.
  • the cooling air is therefore in injected the burner flow channel and as a result of this Injektor strictly advantageously mixed with the fuel-air flow. This proves to be particularly favorable in his Effect on the combustion process and thus in terms lowering of fuel-air ratio and as a result of the pollutant emission.
  • the object is achieved by the invention solved by the burner mentioned above, in which according to the invention the cooling air duct a cooling air outlet in the burner outlet and thus directly into the burner flow channel wherein, during operation of the burner, a pressure gradient in the cooling air duct from the inlet side to the cooling air outlet and to the burner outlet in the burner.
  • the pressure on the component to be cooled is advantageous between the input side and the burner outlet side Print.
  • the cooling air collects in through the burner insert, U-ring, Swirl generator and burner exit wall formed space and It cools these components before the advantageous Cooling air supplied to the burner flow channel at the burner outlet becomes.
  • the pressure gradient is preferably through appropriately arranged seals maintained as effectively as possible.
  • a first seal between the grooved ring and the swirl generator arranged.
  • a second Seal is advantageous between the burner insert and the Burner exit wall arranged.
  • a third seal between the burner insert and the U-ring arranged.
  • the invention also leads to a gas turbine with a top explained burner.
  • FIG 1A is a sectional view of an upper part of a Burner 1 according to the prior art in which the usual open cooling air concept is clarified.
  • the lower Part of the burner 1 according to the prior art is shown in FIG 1A not shown, but results in its principle by a reflection at the symmetry line 2.
  • the burner 1 according to the prior art has a burner insert 3, held by means of a Nutrings 5 on the housing of the gas turbine is. To compensate for uneven thermal expansion of the Swirl generator 7 relative to the grooved ring 5 slidably mounted.
  • the compressor end air formed Combustion air supply 4 and fuel injection 6 schematically shown.
  • the cooling air flow of the burner in the first realized according to the prior art open cooling air concept is represented by arrows.
  • the cooling air flow is by appropriately designed channels in the burner insert 3 and formed in the U-ring 5.
  • a to be cooled H alloyströmtes component such as the burner insert 3, and the mainly heated by heat conduction components, such as Grooved ring 5, swirl generator 7 and burner outlet wall 9 with Cooling air applied. That is, the components 3, 7 and 9 Cooling air is supplied by being flown.
  • the Grooved ring 5 is flowed through by cooling air.
  • the cooling air is again led away from the components and discharged into the environment in the context of the usual open cooling air concept after cooling the components 3, 5, 7, 9.
  • the cooling air is supplied to the combustion chamber, not shown, at a later time, but does not participate in the combustion practically.
  • This open cooling concept has proven disadvantageous.
  • the supply of cooling air directly into the combustion chamber leads to an increase in the fuel-air ratio in the flame, this has higher combustion temperatures and thus increased NO x emissions result.
  • FIG 1B shows the section of a lower part of a particularly preferred embodiment of a burner 11 according to the invention.
  • the upper part of the particularly preferred embodiment of the burner 11 corresponds in principle to the bottom part mirrored on the symmetry line 2.
  • the particularly preferred embodiment of the burner 11 has a burner insert 13, a U-ring 15 and a swirl generator 17.
  • the combustion air supply 14 and the fuel injection 16 are shown schematically.
  • a closed cooling air concept is realized with the cooling air guide 18, which is formed by corresponding channels in and on the burner insert 13, the groove ring 15, the swirl generator 17 and the burner outlet wall 19.
  • the cooling air flow is indicated by corresponding arrows.
  • the burner 11 has a combustion chamber, not shown, of a gas turbine upstream burner outlet 21 of the burner 11.
  • the components to be cooled, ie the burner insert 13, the U-ring 15, the swirl generator 17 and a burner outlet wall 19 are acted upon via the cooling air guide 18 from an input side 23 ago with the cooling air. That is, the cooling air is supplied via the input side 23 to the component 13, 15, 17, and 19 and the component 13, 15, 17, and 19 is flown.
  • the cooling air duct 18 forming channels also the burner insert 13, the U-ring 15 and the swirl generator 17 is flowed through by the cooling air.
  • a closed cooling air concept is realized in the context of the cooling air guide 18. That is, during operation of the burner in the context of the closed cooling air concept is from the input side 23 to the burner outlet 21 of the burner 11 out through a pressure p 1 , p 2 and p 3 characterized pressure gradient maintained in the cooling air duct 18 and the cooling air shown by arrows taking advantage of the pressure gradient p 1 > p 2 > p 3 fed to the burner outlet 21.
  • the burner outlet 21 of the burner 11 is preceded by the combustion chamber, not shown.
  • the cooling air is thus added to the combustion air at a particularly early stage and can contribute to the emission of pollutants.
  • the prevailing pressures p 1 , p 2 , p 3 are shown in FIG 1B.
  • the first pressure p 1 is greater than the second pressure p 2 and the second pressure p 2 is greater than the third pressure p 3 .
  • the first pressure p 1 is formed on the input side 23 and corresponds to the pressure of the air supplied to the burner.
  • the second pressure p 2 is a pressure which is formed in a space 25 which is formed by the burner insert 13, the groove ring 15, the swirl generator 17 and the burner outlet wall 19. In this way, four components 13, 15, 17, 19 are advantageously cooled.
  • the span of the pressure gradient p 1 > p 2 > p 3 is predetermined by the pressure p 3 on the side of the burner outlet 21 and the pressure p 1 on the inlet side 23.
  • the pressure p 2 in the space 25 is mainly maintained and stabilized that the space 25 is sealed with seals 30, 31 and 32 against escape of the cooling air.
  • a first seal 32 between the U-ring 15 and the swirl generator 17 is arranged.
  • a second seal 31 is disposed between the burner insert 13 and the burner exit wall 19.
  • a third seal 30 is disposed between the burner insert 13 and the U-ring 15.
  • a pressure gradient p 1 > p 2 > p 3 is maintained in the cooling air guide 18 during operation of the burner 11 from the input side 23 to the burner outlet 21 and the cooling air by utilizing the pressure gradient p 1 > p 2 > p 3 the Burner outlet 21 supplied.
  • a burner 11 has a component to be cooled 13, 15, 17, 19, a combustion chamber of a gas turbine upstream burner outlet 21 of the burner 11 and a component 13, 15, 17, 19 from an input side 23 forth with cooling air acting on the cooling air duct 18 ,
  • the cooling air duct 18 according to the concept proposed here, a cooling air outlet 27 in the burner outlet 21 and during operation of the burner 11, there is a pressure drop p 1 > p 2 > p 3 in the cooling air duct 18 from the input side 23 to the burner outlet.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
EP04001242A 2004-01-21 2004-01-21 Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant Expired - Lifetime EP1557607B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AT04001242T ATE483138T1 (de) 2004-01-21 2004-01-21 Brenner mit gekühltem bauteil, gasturbine sowie verfahren zur kühlung des bauteils
EP04001242A EP1557607B1 (fr) 2004-01-21 2004-01-21 Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant
DE502004011695T DE502004011695D1 (de) 2004-01-21 2004-01-21 Brenner mit gekühltem Bauteil, Gasturbine sowie Verfahren zur Kühlung des Bauteils

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04001242A EP1557607B1 (fr) 2004-01-21 2004-01-21 Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant

Publications (2)

Publication Number Publication Date
EP1557607A1 true EP1557607A1 (fr) 2005-07-27
EP1557607B1 EP1557607B1 (fr) 2010-09-29

Family

ID=34626480

Family Applications (1)

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EP04001242A Expired - Lifetime EP1557607B1 (fr) 2004-01-21 2004-01-21 Brûleur avec composant refroidi, turbine à gaz et procédé pour refroidir le composant

Country Status (3)

Country Link
EP (1) EP1557607B1 (fr)
AT (1) ATE483138T1 (fr)
DE (1) DE502004011695D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182285A1 (fr) 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019204746A1 (de) 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Hitzeschildkachel mit Dämpfungsfunktion

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
EP0724119A2 (fr) * 1995-01-26 1996-07-31 General Electric Company DÔme pour une chambre de combustion d'une turbine à gaz
DE19757617A1 (de) * 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber
WO1999046540A1 (fr) * 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Chambre de combustion et mode de fonctionnement d'une chambre de combustion
US5956955A (en) * 1994-08-01 1999-09-28 Bmw Rolls-Royce Gmbh Heat shield for a gas turbine combustion chamber
US6035645A (en) * 1996-09-26 2000-03-14 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Aerodynamic fuel injection system for a gas turbine engine
US6530223B1 (en) * 1998-10-09 2003-03-11 General Electric Company Multi-stage radial axial gas turbine engine combustor
WO2003036167A1 (fr) * 2001-10-19 2003-05-01 Alstom Technology Ltd Bruleur a gaz de synthese

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
US5956955A (en) * 1994-08-01 1999-09-28 Bmw Rolls-Royce Gmbh Heat shield for a gas turbine combustion chamber
EP0724119A2 (fr) * 1995-01-26 1996-07-31 General Electric Company DÔme pour une chambre de combustion d'une turbine à gaz
US5941076A (en) * 1996-07-25 1999-08-24 Snecma-Societe Nationale D'etude Et De Construction De Moteurs D'aviation Deflecting feeder bowl assembly for a turbojet engine combustion chamber
US6035645A (en) * 1996-09-26 2000-03-14 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Aerodynamic fuel injection system for a gas turbine engine
DE19757617A1 (de) * 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
WO1999046540A1 (fr) * 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Chambre de combustion et mode de fonctionnement d'une chambre de combustion
US6530223B1 (en) * 1998-10-09 2003-03-11 General Electric Company Multi-stage radial axial gas turbine engine combustor
WO2003036167A1 (fr) * 2001-10-19 2003-05-01 Alstom Technology Ltd Bruleur a gaz de synthese

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182285A1 (fr) 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
US9074771B2 (en) 2008-10-29 2015-07-07 Siemens Aktiengesellschaft Burner inserts for a gas turbine combustion chamber and gas turbine

Also Published As

Publication number Publication date
EP1557607B1 (fr) 2010-09-29
DE502004011695D1 (de) 2010-11-11
ATE483138T1 (de) 2010-10-15

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