EP3620718A1 - Gasturbinenbrenner mit brennstoff-luft-pilotmischung - Google Patents

Gasturbinenbrenner mit brennstoff-luft-pilotmischung Download PDF

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Publication number
EP3620718A1
EP3620718A1 EP18193084.3A EP18193084A EP3620718A1 EP 3620718 A1 EP3620718 A1 EP 3620718A1 EP 18193084 A EP18193084 A EP 18193084A EP 3620718 A1 EP3620718 A1 EP 3620718A1
Authority
EP
European Patent Office
Prior art keywords
pilot
burner
mixing
mixing tube
fuel
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Withdrawn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
EP18193084.3A
Other languages
English (en)
French (fr)
Inventor
Anton Berg
Atanu Kumar Kundu
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 EP18193084.3A priority Critical patent/EP3620718A1/de
Priority to EP19769056.3A priority patent/EP3821174B1/de
Priority to PCT/EP2019/073185 priority patent/WO2020048880A1/en
Publication of EP3620718A1 publication Critical patent/EP3620718A1/de
Withdrawn legal-status Critical Current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
    • F23R3/28—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
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2203/00—Gaseous fuel burners
    • F23D2203/007—Mixing tubes, air supply regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the invention relates to a burner according to the features of the preamble of claim 1.
  • Such burners are preferably used for firing the combustion chamber of a gas turbine.
  • Such burners are known from EP 1 389 713 B1 and comprise a swirl generator and a downstream mixing tube.
  • the burner head is provided with a pilot burner system to support the main flame.
  • the pilot burner system comprises a mixing cavity for mixing pilot fuel and assist air.
  • the mixing cavity of the known burner is of a pure circumferential shape. Since such a design bears the risk for the pilot flame to burn inside the mixing cavity
  • EP 2 268 975 B1 proposes a solution with swirler wings being arranged in the vicinity of the pilot fuel/air mix outlet nozzles.
  • pilot flame is an external air assisted diffusion like flame that has inherent flame stability but can also create high NO x emission due to this diffusion mode combustion.
  • combustor dump locations contribute to flame stabilization as will be shown in Figure 3 .
  • the object of the present invention is to improve a burner of the above type in such a way that NO x emission is reduced.
  • the present invention solves the above problem by providing a burner with a burner head comprising a main mixing tube for premixing combustion air and fuel, wherein the main mixing tube is provided with a pilot burner system in its downstream part, wherein the pilot burner system comprises an annular mixing cavity with an entrance for air in its upstream end, with an entrance for pilot fuel and with an outlet nozzle in its downstream end, wherein a pilot mixing tube extends inside the mixing cavity between the air entrance and the outlet nozzle with a pilot mixing tube length exceeding a distance between the upstream and the downstream ends of the mixing cavity.
  • the non-premixed behavior of the pilot flame is one of the major sources of NO x .
  • the extended mixing path inside the mixing cavity of the inventive burner improves fuel and air mixing and reduces the formation of NO x . Further premixing of the pilot stage is possible when the pilot flame has an additional flame stabilization point.
  • the present invention is intended to increase the pilot fuel mixing and inherently to reduce the NO x without affecting the flame stability.
  • the mixing cavity comprises a conical front surface facing away from the burner axis and the outlet nozzle is arranged in that conical front surface with an injection angle perpendicular to the front surface.
  • pilot fuel entrance of the mixing cavity is in its downstream part and a pilot fuel entrance of the pilot mixing tube is in its upstream part.
  • a cooling channel is arranged in at least a part of a radially outer wall and the downstream end of the mixing cavity.
  • Yet another preferred embodiment of the present invention is characterized in that the cooling channel opens out at the conical front surface at an inner position compared to the outlet nozzle as seen in a radial direction of the burner.
  • the cooling channel begins at an upstream part of the mixing cavity.
  • pilot mixing tube is a spiral tubing arrangement.
  • the pilot mixing tube comprises secondary tubes that merge before opening out into the outlet nozzle.
  • the pilot mixing tube comprises steps.
  • pilot mixing tube is fully integrated with the mixing cavity, especially when the pilot burner system is additively manufactured.
  • the present invention additionally relates to an annular combustion chamber of a gas turbine, which is characterized in that at least two, preferably at least 10 burners as described above are arranged within the combustion chamber.
  • the mixing of fuel and air can be improved by introducing additively manufactured pilot fueling arrangement with additional mixing length.
  • mixing at the pilot burner stage exit can be controlled more efficiently.
  • the overall fuel-air mixing is improved.
  • the enhanced mixing can produce lower NO x emission without affecting the combustion stability.
  • a variable mixing length is possible for different fuels. Variable location fuel injection possibility can widen the fuel flexibility of the pilot stage combustion.
  • the relatively small partially premixed pilot arrangement of the prior art can be replaced with a cavity filled with fuel and tube arrangements according to the invention.
  • pilot burner system 3 comprising an annular mixing cavity 4 with an entrance 5 for air in its upstream end, with an entrance 6 for pilot fuel and with an outlet nozzle 7 in its downstream end.
  • a pilot mixing tube 8 extends inside the mixing cavity 4 between the air entrance 5 and the outlet nozzle 7.
  • the pilot mixing tube 8 length exceeds a distance between the upstream and the downstream ends of the mixing cavity 4 which is achieved by a meandering pilot mixing tube 8.
  • the pilot mixing tube 8 is fully integrated with the mixing cavity 4 and given the geometry is suitable for being additively manufactured.
  • the mixing cavity 4 comprises a conical front surface 9 facing away from the burner axis 10 (see figure 3 ).
  • the outlet nozzle 7 is arranged in that conical front surface 9 with an injection angle perpendicular to the front surface 9.
  • pilot fuel 19 is provided through a channel 27 arranged in the wall of the main mixing tube 2 which is also the radially inner wall of the mixing cavity 4 and enters the mixing cavity 4 at its downstream part where it travels in the opposite direction and enters the pilot mixing tube 8 in its upstream part so that the pilot mixing tube 8 carries the air and the fuel.
  • the fuel supply is indicated by lines and arrows in figure 5 .
  • the fuel injection holes at the pilot fuel entrance 11 of the pilot mixing tube 8 can be of different cross section like oval/triangular or circular to get the penetration. Additionally, swirl can also be introduced in the fuel holes if required.
  • Figure 6 shows a cut through an alternative embodiment of the annular mixing cavity 4 for supplying fuel and air in the pilot burner system 3 with more safety features or film air to protect the metal.
  • Figure 6 shows a cooling channel 12 arranged in at least a part of a radially outer wall 13 and the downstream end of the mixing cavity 4 for a small stream of air.
  • the cooling channel 12 opens out at the conical front surface 9 at an inner position compared to the outlet nozzle 7 as seen in a radial direction of the burner 1.
  • the cooling channel 12 begins at an upstream part of the mixing cavity 4. Further, the front surface 9 is cooled by the fuel which is then introduced inside the mixing cavity 4 for mixing.
  • Figure 7 shows the pilot mixing tube 8 realized as a spiral tubing arrangement inside the mixing cavity 4.
  • Figure 8 shows a multiple pilot tube arrangement where the pilot mixing tubes 8 comprise steps.
  • the step type tubing can be in X-Y or X-Z plane.
  • the X-Z plane which is parallel to the burner outer surface, opens many possibilities to place the pilot mixing tube bundles.
  • Figure 9 shows a pilot fuel arrangement where secondary tubes 14 combine inside the mixing cavity 4 before opening out into the outlet nozzle 7.
  • pilot mixing tube 8 arrangements can be incorporated based on design requirements.
  • the location of the entrance for pilot fuel of the mixing cavity 4 can be varied to achieve a specific degree of mixing of fuel and air.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP18193084.3A 2018-09-07 2018-09-07 Gasturbinenbrenner mit brennstoff-luft-pilotmischung Withdrawn EP3620718A1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP18193084.3A EP3620718A1 (de) 2018-09-07 2018-09-07 Gasturbinenbrenner mit brennstoff-luft-pilotmischung
EP19769056.3A EP3821174B1 (de) 2018-09-07 2019-08-30 Gasturbinenbrenner mit brennstoff-luft-pilotmischung
PCT/EP2019/073185 WO2020048880A1 (en) 2018-09-07 2019-08-30 Gas turbine burner with pilot fuel-air mixing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18193084.3A EP3620718A1 (de) 2018-09-07 2018-09-07 Gasturbinenbrenner mit brennstoff-luft-pilotmischung

Publications (1)

Publication Number Publication Date
EP3620718A1 true EP3620718A1 (de) 2020-03-11

Family

ID=63528543

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18193084.3A Withdrawn EP3620718A1 (de) 2018-09-07 2018-09-07 Gasturbinenbrenner mit brennstoff-luft-pilotmischung
EP19769056.3A Active EP3821174B1 (de) 2018-09-07 2019-08-30 Gasturbinenbrenner mit brennstoff-luft-pilotmischung

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP19769056.3A Active EP3821174B1 (de) 2018-09-07 2019-08-30 Gasturbinenbrenner mit brennstoff-luft-pilotmischung

Country Status (2)

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EP (2) EP3620718A1 (de)
WO (1) WO2020048880A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113440978A (zh) * 2021-07-08 2021-09-28 山东红石环保科技有限公司 一种工业废气处理装置及方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1389713A1 (de) 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Stromabwärtiger Pilotringbrenner für Vormischbrenner
EP2268975B1 (de) 2008-04-15 2016-12-14 Siemens Aktiengesellschaft Brenner
EP3290804A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brenner mit kraftstoff- und luftzufuhr in einer wand des brenners

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1389713A1 (de) 2002-08-12 2004-02-18 ALSTOM (Switzerland) Ltd Stromabwärtiger Pilotringbrenner für Vormischbrenner
EP2268975B1 (de) 2008-04-15 2016-12-14 Siemens Aktiengesellschaft Brenner
EP3290804A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brenner mit kraftstoff- und luftzufuhr in einer wand des brenners

Also Published As

Publication number Publication date
WO2020048880A1 (en) 2020-03-12
EP3821174B1 (de) 2023-08-23
EP3821174A1 (de) 2021-05-19

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