EP0832399B1 - Katalytische zündbrenner einer gasturbine - Google Patents

Katalytische zündbrenner einer gasturbine Download PDF

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Publication number
EP0832399B1
EP0832399B1 EP96917334A EP96917334A EP0832399B1 EP 0832399 B1 EP0832399 B1 EP 0832399B1 EP 96917334 A EP96917334 A EP 96917334A EP 96917334 A EP96917334 A EP 96917334A EP 0832399 B1 EP0832399 B1 EP 0832399B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
catalytic
main
gas turbine
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.)
Revoked
Application number
EP96917334A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0832399A1 (de
Inventor
Erich Hums
Nicolas Vortmeyer
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=7764161&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0832399(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP0832399A1 publication Critical patent/EP0832399A1/de
Application granted granted Critical
Publication of EP0832399B1 publication Critical patent/EP0832399B1/de
Anticipated expiration legal-status Critical
Revoked legal-status Critical Current

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Classifications

    • 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 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • 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 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • F23C13/08—Apparatus in which combustion takes place in the presence of catalytic material characterised by the catalytic material
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
    • 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
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines

Definitions

  • the invention relates to a burner, in particular for a gas turbine in which a catalytic auxiliary burner is provided to stabilize a main burner.
  • a burner in particular for a gas turbine in which a catalytic auxiliary burner is provided to stabilize a main burner.
  • Such burners are shown, for example, in document EP-A-491 481.
  • Fuel is, in particular, natural gas, coal gas or another gaseous hydrocarbon and / or hydrogen containing Mixture provided. Such a mixture is also suitable or a fossil fuel in liquid form.
  • nitrogen oxides NO x are formed as particularly undesirable combustion products. In addition to sulfur dioxide, these nitrogen oxides are the main cause of the environmental problem of acid rain.
  • One is therefore - also due to strict legal limit values for NO x emissions - willing to keep the NO x emissions of a burner in a gas turbine particularly low without significantly influencing the performance of the burner or the gas turbine.
  • the reduction in flame temperature in the Burner as nitrogen oxide reducing.
  • This is the fuel or also supplied compressed and preheated Fresh air steam added or water in the combustion chamber injected.
  • Such measures that reduce the nitrogen oxide emissions of the Reduce Brenners per se, are used as primary measure Nitrogen oxide reduction.
  • a burner to produce one Pilot flame is usually a diffusion burner that represents a not insignificant source of nitrogen oxide. Given the environmental problems caused by the nitrogen oxides and due to strict legal requirements for nitrogen oxide emissions One strives therefore, every little source of nitrogen oxide to avoid or at least reduce their nitrogen oxide emissions.
  • the invention is therefore based on the object of a burner, Specify in particular for a gas turbine in which the Device for generating a pilot flame particularly low in nitrogen oxide is working.
  • a Burner for the combustion of a fuel, in the flow direction of the fuel in a flow channel before the fuel outlet of a main burner
  • Fuel outlet of a catalytic support burner for stabilization of the main burner under catalytic combustion a pilot fuel flow is provided and that based on the cross section of the flow channel for fuel the catalytic auxiliary burner central and Main burners are arranged coronally. This is particularly so for a homogeneous distribution of the pilot flame radially Direction advantageous, so that the combustion of the main fuel stream done on a uniform front can.
  • the burner uses catalytic combustion of the pilot fuel flow to stabilize or support the Main burner.
  • the pilot fuel flow through a preforming stage is led to the catalytic support burner. To this Way will lower the catalytic ignition temperature of the pilot fuel flow reached because in the preforming stage the fuel into easily ignited compounds is decomposed.
  • the preforming stage for example alcohols such as methanol, aldehydes and Hydrogen formed.
  • pilot fuel flow is mixed with ambient and / or compressor air.
  • NO x emissions of the pilot burner can be further reduced by setting the volume ratios of fuel / preformed fuel to ambient and / or compressor air.
  • this Distance can preferably be about 0.75 to 2 m.
  • the main burner as a catalytic Main burner is running.
  • Such a burner records as well as the catalytic auxiliary burner by comparative low nitrogen oxide emissions.
  • FIG. 1 shows the burner part 2 in a schematic representation a gas turbine not shown here.
  • the burner part 2 comprises a flow channel in the exemplary embodiment 4, in which a catalytic support burner 6 and a catalytic Main burner 8 are installed.
  • the catalytic support burner 6 and the main catalytic burner 8 are rotationally symmetrical arranged to the axis of symmetry 10 of the flow channel 4.
  • pilot fuel stream 22 originally consists of the same natural gas / air-gas mixture 18, 20, which, however, in a preforming stage 24 is preformed.
  • the one in the Support burner 6 incoming preformed pilot fuel flow 22 may also be referred to as an easily ignited pilot fuel stream become.
  • the preforming of the natural gas / air mixture 18, 20 takes place on a noble metal-containing catalyst, which For example, has honeycomb form, as the main component of titanium dioxide and as catalytically active components platinum and Rhodium includes.
  • the catalyst is not shown here Installed in the preforming stage 24.
  • the catalyst in the preforming stage 24th also be a heat exchanger upstream, in order to Preforming stage entering natural gas / air mixture 18, 20 warm up and so the effectiveness of the catalyst in the Raise preformation level 24.
  • Form during preforming is comparatively easy from the natural gas 18 igniting substances such as methanol, aldehyde and hydrogen.
  • the fuel outlet is the catalytic one Support burner 6 in the flow direction of the fuel gas 16 at a distance d of about 1 m before the fuel outlet of the Main catalytic burner 8 arranged.
  • the catalytic Support burner 6 in the exemplary embodiment comprises a honeycomb catalyst, the basic component is at least one of the substances Has titanium dioxide, silicon dioxide and zirconium oxide. Basically, all are catalytically active components Precious metals and metal oxides are suitable, which are strongly oxidizing Have an effect on the fuels mentioned. There are for example precious metals such as platinum, rhodium, rhenium, Iridium, and metal oxides, such as. B.
  • transition metal oxides Vanadium oxide, tungsten oxide, molybdenum oxide, chromium oxide, Copper oxide, manganese oxide and oxides of the lanthanoids, e.g. Cerium oxide.
  • Metal ions exchanged zeolites can also be used and spinel-type metal oxides can be used.
  • the pilot fuel flow entering the catalytic auxiliary burner 6 22 is due to the catalytically active substances oxidizes and burns with a pilot flame 26. Because the fuel outlet of the auxiliary burner 6 in the flow direction of the fuel gas 16 the distance d before the fuel outlet of the Main burner 8 is arranged, it is safely ensured that the main flame 28 is not in the main catalytic burner 8 or even in the areas in front of the catalytic burners 6, 8 can strike back. The distance d is in the selected Embodiment about 1 m.
  • the catalyst material in the main burner 8 differs not from the catalyst material of the auxiliary burner 6.
  • catalytically particularly active substance in relation to the oxidation of the hydrocarbons contained in the fuel 16 each 1% by weight of platinum and rhodium and 2% by weight of vanadium oxide, Chromium oxide and tungsten oxide are provided.
  • the burner exhaust gas emerging from the burner part 2 has one particularly low nitrogen oxide content because, on the one hand the fuel 16 is catalytically burned in the main burner 8 and because the pilot flame 26 is also catalytic Combustion of pilot fuel stream 22 in the auxiliary burner 6 is generated.
  • the main catalytic burner 8 can also be used as the main burner from the prior art known diffusion burners or swirl-stabilized premix burners be used.
  • FIG. 2 shows a top view of the flow channel 4, in which the arrangement of the main burner 8 as a catalytically active honeycomb catalyst can be seen in a schematic representation.
  • honeycomb catalysts usually have a cell count of 0.62 to 15.5 cells per cm 2 (4 to 100 cells per inch 2 ) and have a wall thickness of the webs of 0.5 to 5 mm.
  • metallic plate catalysts or, in principle, plate catalysts.
  • the catalytic support burner 6 arranged centrally in the top view according to FIG. 2 is usually identical to the geometry of the main catalytic burner 8 with regard to its geometry of the channels.
  • FIGS. 3 and 4 show an exemplary embodiment of the invention, in which the main catalytic burner 8 recognizable from FIG. 1 and FIG. 2 is replaced by a non-catalytic main burner, which has guide blades 31 as important distinguishing features. These guide vanes 32 impart a swirl to the fuel / air mixture flowing through, which stabilizes the combustion that starts in this mixture.
  • the non-catalytic main burner is characterized by a particularly low operational pressure loss and by a particular simplicity of construction, which particularly recommends this main burner for use in a gas turbine. Because the main burner causes premix combustion, a comparatively low NO x emission is guaranteed in any case.
  • the pilot burner 6 is also designed as a catalytic auxiliary burner 6 in the exemplary embodiment according to FIGS. 3 and 4, it is in any case not an essential source of nitrogen oxides; accordingly, the burner according to FIG. 3 and FIG. 4 is also qualified as a burner with particularly low NO x emissions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Gas Burners (AREA)
EP96917334A 1995-06-12 1996-06-11 Katalytische zündbrenner einer gasturbine Revoked EP0832399B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19521309 1995-06-12
DE19521309 1995-06-12
PCT/DE1996/001019 WO1996041991A1 (de) 1995-06-12 1996-06-11 Katalytische zündbrenner einer gasturbine

Publications (2)

Publication Number Publication Date
EP0832399A1 EP0832399A1 (de) 1998-04-01
EP0832399B1 true EP0832399B1 (de) 2000-01-12

Family

ID=7764161

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96917334A Revoked EP0832399B1 (de) 1995-06-12 1996-06-11 Katalytische zündbrenner einer gasturbine

Country Status (7)

Country Link
EP (1) EP0832399B1 (cs)
JP (1) JP4063871B2 (cs)
DE (1) DE59604180D1 (cs)
ES (1) ES2142588T3 (cs)
IN (1) IN191368B (cs)
RU (1) RU2149317C1 (cs)
WO (1) WO1996041991A1 (cs)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005054442B4 (de) * 2004-11-17 2011-04-07 Mitsubishi Heavy Industries, Ltd. Brennkammer für eine Gasturbine
US8540508B2 (en) 2003-08-13 2013-09-24 Siemens Aktiengesellschaft Method for the combustion of a fluid fuel, and burner, especially of a gas turbine, for carrying out said method

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3543717B2 (ja) * 2000-02-18 2004-07-21 日産自動車株式会社 触媒燃焼器
WO2004020901A1 (de) 2002-08-30 2004-03-11 Alstom Technology Ltd Hybridbrenner und zugehöriges betriebsverfahren
JP5732135B2 (ja) * 2011-08-17 2015-06-10 大陽日酸株式会社 Ｈ２用バーナの燃焼方法
US9322557B2 (en) * 2012-01-05 2016-04-26 General Electric Company Combustor and method for distributing fuel in the combustor

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2500064B2 (fr) * 1981-02-17 1985-11-08 Snecma Dispositif d'allumage de carburant injecte dans un milieu gazeux en ecoulement rapide
JPS5963407A (ja) * 1982-10-01 1984-04-11 Matsushita Electric Ind Co Ltd 触媒燃焼器
DE3474714D1 (en) * 1983-12-07 1988-11-24 Toshiba Kk Nitrogen oxides decreasing combustion method
JPS61276627A (ja) * 1985-05-30 1986-12-06 Toshiba Corp ガスタ−ビン燃焼器
US4870824A (en) * 1987-08-24 1989-10-03 Westinghouse Electric Corp. Passively cooled catalytic combustor for a stationary combustion turbine
US4825658A (en) * 1987-12-11 1989-05-02 General Electric Company Fuel nozzle with catalytic glow plug
GB9027331D0 (en) * 1990-12-18 1991-02-06 Ici Plc Catalytic combustion
US5634784A (en) * 1991-01-09 1997-06-03 Precision Combustion, Inc. Catalytic method
US5165224A (en) * 1991-05-15 1992-11-24 United Technologies Corporation Method and system for lean premixed/prevaporized combustion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8540508B2 (en) 2003-08-13 2013-09-24 Siemens Aktiengesellschaft Method for the combustion of a fluid fuel, and burner, especially of a gas turbine, for carrying out said method
DE102005054442B4 (de) * 2004-11-17 2011-04-07 Mitsubishi Heavy Industries, Ltd. Brennkammer für eine Gasturbine

Also Published As

Publication number Publication date
WO1996041991A1 (de) 1996-12-27
IN191368B (cs) 2003-11-29
JPH11509307A (ja) 1999-08-17
ES2142588T3 (es) 2000-04-16
RU2149317C1 (ru) 2000-05-20
JP4063871B2 (ja) 2008-03-19
EP0832399A1 (de) 1998-04-01
DE59604180D1 (de) 2000-02-17

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