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EP0832398A1 - Chambre de combustion catalytique pour turbine a gaz - Google Patents

Chambre de combustion catalytique pour turbine a gaz

Info

Publication number
EP0832398A1
EP0832398A1 EP96915991A EP96915991A EP0832398A1 EP 0832398 A1 EP0832398 A1 EP 0832398A1 EP 96915991 A EP96915991 A EP 96915991A EP 96915991 A EP96915991 A EP 96915991A EP 0832398 A1 EP0832398 A1 EP 0832398A1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustion chamber
burner
burner according
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.)
Granted
Application number
EP96915991A
Other languages
German (de)
English (en)
Other versions
EP0832398B1 (fr
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
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP0832398A1 publication Critical patent/EP0832398A1/fr
Application granted granted Critical
Publication of EP0832398B1 publication Critical patent/EP0832398B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • the invention relates to a burner, in particular for a gas turbine, with a catalytic combustion chamber.
  • a hydrocarbon and / or hydrogen-containing energy carrier is provided as a fuel both in liquid and in gaseous form.
  • a fuel is, for example, natural gas, petroleum or methane.
  • Such a burner can preferably be used in a gas turbine.
  • a gas turbine usually consists of a compressor part, a burner part and a turbine part.
  • the compressor part and the turbine part are usually located on a common shaft which at the same time drives a generator for generating electricity.
  • preheated fresh air is burned with a fuel of the type mentioned.
  • the hot burner exhaust gas is fed to the turbine section and expanded there.
  • Siemens AG May 1994, Order No. A 96001-U 124-V 1-7600, provides detailed information on the construction and use of a gas turbine.
  • nitrogen oxides NO x also arise as particularly undesirable combustion products.
  • these nitrogen oxides are the main cause of the environmental problem of acid rain. It is therefore - also due to strict legal limit values for NO x emissions - willing to keep the NO x emissions from a gas turbine particularly low and at the same time largely unaffected by the performance of the gas turbine.
  • reducing the flame temperature in the burner reduces nitrogen oxide.
  • water vapor is added to the fuel or the compressed and preheated fresh air or water is injected into the combustion chamber. Measures that reduce nitrogen oxide emissions per se are referred to as primary measures for nitrogen oxide reduction.
  • GB 2 268 694 A provides a catalytic combustion chamber, the ignition temperature of a fuel being lowered by a partial catalytic oxidation.
  • the catalysts provided for this purpose are installed transversely to the flow direction of the fuel and extend over the entire flow cross section. This gives a high flow resistance.
  • any nitrogen oxide reduction, primary or secondary, provided there results in a loss of performance or a loss in the overall efficiency of the gas turbine system.
  • the invention is therefore based on the object of specifying a burner, in particular for a gas turbine, which is distinguished by particularly low nitrogen oxide emissions and, at the same time, a particularly high efficiency.
  • This object is achieved according to the invention with a burner in which a catalytic combustion chamber is provided, the combustion chamber having an essentially cylindrical expansion in the direction of flow of a fuel and the wall facing the fuel having a catalytically active coating for oxidizing the fuel.
  • a particularly low nitrogen oxide content of the burner exhaust gas is achieved by the catalytically induced combustion of the fuel.
  • the coating of the wall of the combustion chamber does not increase the flow resistance, so that particularly high efficiencies can be achieved in a gas turbine with such a catalytic combustion chamber.
  • the essentially cylindrical shape of the catalytic combustion chamber and the catalytically active coating of the wall contribute to the fuel igniting starting from the wall and a spreading of the flame front from the catalytically active surface of the wall into the free Flow of the fuel gas is possible.
  • the cylindrical shape in particular contributes to an essentially concentric and thus homogeneous distribution of the flame front, which results in complete and uniform combustion of the fuel.
  • the process of forming a largely rotationally symmetrical flame front in the combustion chamber is further supported if the ring or rings are arranged exclusively in the outer region of the essentially circular cross section of the combustion chamber.
  • a fuel comprising a main fuel stream, a preformed partial fuel stream and air can be fed to the combustion chamber.
  • the main fuel flow consists mostly of natural gas and / or coal gas and / or hydrogen.
  • the preformed partial fuel stream is a partial stream which is separated from the main fuel stream and passed through a preforming stage.
  • natural gas ignites catalytically easier than natural gas, such as e.g. Alcohols, aldehydes and hydrogen.
  • a fuel gas mixed with such a preformed partial fuel flow therefore has excellent catalytic ignitability.
  • the ignitability of the fuel introduced into the catalytic combustion chamber can provide that a preformed partial fuel stream, optionally premixed with air, enters the combustion chamber through bores in the wall.
  • a preformed partial fuel stream optionally premixed with air
  • the wall can be cooled.
  • the wall can be cooled, for example, with air, at the same time preheating the air. This preheated air can, for example, be subsequently compressed in the compressor part to the combustion chamber inlet pressure.
  • the catalytic effect of the catalytically active coating occurs particularly advantageously when the catalytically active coating titanium dioxide, which is preferably flame and plasma sprayed, and a noble metal component selected from platinum, rhodium, palladium, iridium, rhenium and / or a metal oxide component , consisting of one or more transition metal oxides.
  • Suitable transition metal oxides are those oxides which have a strongly oxidizing catalytic effect, e.g. Copper oxide, chromium oxide, iron oxide, molybdenum oxide, tungsten oxide, vanadium oxide, manganese oxide, cerium oxide and other oxides of lanthanides.
  • FIG. 1 shows a schematic representation of the burner of a gas turbine with a catalytic combustion chamber
  • FIG. 2 shows a schematic representation of the burner of a gas turbine according to FIG. 1 with a slight difference
  • Figure 1 modified catalytic combustion chamber
  • FIG. 3 shows a catalytic combustion chamber in cross section.
  • FIGS. 1 to 3 the same parts have the same reference numbers.
  • 1 shows a gas turbine 2 which comprises a compressor part 4, a burner part 6 and a turbine part 7.
  • the burner part 6 comprises a catalytic combustion chamber 8, the wall 10 of which has a catalytically active coating 12.
  • the catalytic combustion chamber 8 has a circular cross section.
  • a fuel gas flows into the catalytic combustion chamber 8 as fuel 14, which in the exemplary embodiment consists of air 16 compressed in the compressor part 4, a main fuel stream 18 and a preformed partial fuel stream 20.
  • This preformed partial fuel stream 20 is separated from an original fuel stream 22 and passed through a preforming stage 24.
  • the fuel stream 22 consists of natural gas, from which in the preforming stage 24 substances which ignite catalytically more easily than natural gas, such as e.g. Alko ⁇ hole, aldehydes and hydrogen are formed.
  • the preforming stage 24 comprises a ceramic honeycomb catalyst based on titanium dioxide, which is not shown any further and which additionally comprises a noble metal component consisting of platinum and palladium applied superficially to the honeycomb catalyst.
  • the catalytically active coating 12 on the wall 10 of the catalytic combustion chamber 8 consists of a flame-sprayed titanium dioxide layer with a thickness of approximately 500 ⁇ m, on which are additionally deposited noble metal particles of platinum, rhodium and palladium as well as particles of transition metal oxides, such as cerium oxide. Vanadium oxide and chromium oxide are applied.
  • a flame-sprayed titanium dioxide a plasma-sprayed titanium dioxide layer can also be provided. Both layers are distinguished by their great strength on the wall 10 of the catalytic combustion chamber 8, which is usually made of an austenitic steel.
  • the upstream flame front 26 formed in this way is largely rotationally symmetrical, so that the temperature distribution in the catalytic combustion chamber 8 along the main flow direction has approximately circular isotherms with respect to the cross section. This is advantageous for a uniform and low-pollutant combustion of the fuel 14.
  • the fuel 14 catalytically burned in this way enters the turbine part 7 of the gas turbine 2 at a temperature of approximately 1100 ° C. and is expanded there.
  • the thermal energy transmitted in the turbine part is used to drive a generator for generating electricity, which is not shown here.
  • This generator is arranged on the same shaft (not shown further here) as the gas turbine 2.
  • the burner exhaust gas 30 leaving the turbine part 7 is particularly low in nitrogen oxide due to the catalytic combustion of the fuel gas 14 and has a nitrogen oxide content of approximately 70 ppm.
  • the burner exhaust gas 30 can be used in a waste heat steam generator (not shown here) for steam generation.
  • FIG. 2 shows a schematic representation of a gas turbine 2 'slightly modified compared to FIG. 1. The modifications are limited to the design of the catalytic combustion chamber 8.
  • the catalytic combustion chamber 8 'shown in FIG. 2 differs from FIG. 1 in that 10 bores 32 are provided in the wall through which the preformed fuel - partial flow 20 and air 16 enter the combustion chamber 8 '.
  • the first advantage is that the fuel mixture with the lowest catalytic ignition temperature temperature enters the combustion chamber 8 'directly at the catalytically active coating 12 and therefore ignites comparatively spontaneously. This measure therefore contributes particularly to the stabilization of the upstream flame front 26.
  • the second advantage is that the walls 10 are cooled by the flowing mixture of preformed partial fuel flow 20 and air 16. This cooling also reduces the thermal load on the catalytically active coating 12, which has a favorable effect on the durability of this coating 12. Cooling of the wall 10 can alternatively also be achieved in a manner not shown here by means of a flow of air 16 which enters the compressor part 4.
  • FIG. 3 shows a schematic representation of the cross section of a catalytic combustion chamber 34 modified compared to FIGS. 1 and 2.
  • the wall 10 and the catalytically active coating 12 for the oxidation of the fuel 14 can again be seen.
  • the oxidation of the fuel is understood to mean, of course, that the fuel 14, 22 is oxidized and the oxygen which is brought in via the air 16 and is required for combustion is reduced.
  • the catalytically active coating 12 for the oxidation of the fuel gas 14 therefore means the coating which induces the entire combustion process with oxidized and reduced combustion products.
  • the combustion chamber 34 has three rings 36 arranged concentrically. These concentric rings 36 are thin strips of sheet metal, consisting of the material of the wall 10.
  • the rings 36 have the same catalytically active coating 12 with which the wall 10 of the combustion chamber 34 is also coated. For the sake of clarity of the illustration, the catalytically active coating 12 is only shown in a selected quadrant.
  • the webs 38 holding the rings 36 also have this catalytically active coating 12.
  • the rings 36 are exclusively in the outer Region of the substantially circular cross-section of the combustion chamber 34 is arranged to restrict the initial ignition of the fuel 14 to the outer region of the cross-section of the combustion chamber 34. The flame front then extends automatically into the free flow of the fuel gas 14.
  • the rings 36 with the catalytically active coating 12 thus contribute to stabilizing the flame front and ensuring complete and therefore particularly low-emission combustion.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Catalysts (AREA)

Abstract

Selon l'invention, il est prévu un brûleur comportant une chambre de combustion catalytique. Dans le sens d'écoulement d'un combustible, cette chambre de combustion présente un évasement sensiblement cylindrique, et sur la paroi qui fait face au combustible, un revêtement à action catalytique pour oxyder ledit combustible. La combustion d'un combustible induite par voie catalytique permet de parvenir à une teneur particulièrement réduite en oxyde d'azote des gaz brûlés du brûleur. Simultanément, ce revêtement de la paroi permet de ne pas augmenter la résistance à l'écoulement dans le brûleur, contrairement aux mesures de base connues visant à réduire les émissions d'oxyde d'azote. L'utilisation de ce type de brûleur dans une turbine à gaz permet par conséquent d'obtenir un rendement particulièrement élevé, avec des émissions d'oxyde d'azote réduites. Cette invention s'utilise notamment dans toutes les turbines à gaz.
EP96915991A 1995-06-12 1996-06-11 Chambre de combustion catalytique pour turbine a gaz Expired - Lifetime EP0832398B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19521356 1995-06-12
DE1995121356 DE19521356C2 (de) 1995-06-12 1995-06-12 Gasturbine, umfassend einen Verdichterteil, einen Brennerteil und einen Turbinenteil
PCT/DE1996/001020 WO1996041992A1 (fr) 1995-06-12 1996-06-11 Chambre de combustion catalytique pour turbine a gaz

Publications (2)

Publication Number Publication Date
EP0832398A1 true EP0832398A1 (fr) 1998-04-01
EP0832398B1 EP0832398B1 (fr) 2000-01-12

Family

ID=7764194

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96915991A Expired - Lifetime EP0832398B1 (fr) 1995-06-12 1996-06-11 Chambre de combustion catalytique pour turbine a gaz

Country Status (6)

Country Link
EP (1) EP0832398B1 (fr)
JP (1) JPH11507433A (fr)
DE (2) DE19521356C2 (fr)
ES (1) ES2142587T3 (fr)
RU (1) RU2143643C1 (fr)
WO (1) WO1996041992A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19654022A1 (de) * 1996-12-21 1998-06-25 Abb Research Ltd Verfahren zum Betrieb einer Gasturbogruppe
DE10061526A1 (de) * 2000-12-11 2002-06-20 Alstom Switzerland Ltd Vormischbrenneranordnung zum Betrieb einer Brennkammer
DE10061527A1 (de) 2000-12-11 2002-06-13 Alstom Switzerland Ltd Vormischbrenneranordnung mit katalytischer Verbrennung sowie Verfahren zum Betrieb hierzu
RU2232349C1 (ru) * 2002-12-23 2004-07-10 Государственное унитарное предприятие Тушинское машиностроительное конструкторское бюро "Союз" - дочернее предприятие Федерального государственного унитарного предприятия "Российская самолето-строительная корпорация "МиГ" Каталитический воспламенитель
US7007487B2 (en) * 2003-07-31 2006-03-07 Mes International, Inc. Recuperated gas turbine engine system and method employing catalytic combustion
RU2260156C2 (ru) * 2003-08-25 2005-09-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Жаровая труба камеры сгорания
RU2250414C1 (ru) * 2003-09-10 2005-04-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Камера сгорания
RU2342601C1 (ru) * 2007-06-14 2008-12-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Газотурбинная установка регенеративного цикла с каталитической камерой сгорания
JP4538077B2 (ja) * 2008-06-13 2010-09-08 川崎重工業株式会社 希薄燃料吸入ガスタービン
DE102008056741A1 (de) * 2008-11-11 2010-05-12 Mtu Aero Engines Gmbh Verschleissschutzschicht für Tial
JP5380488B2 (ja) 2011-05-20 2014-01-08 株式会社日立製作所 燃焼器
WO2016056941A1 (fr) * 2014-10-09 2016-04-14 Дмитрий Александрович ЛЕБЕДЕВ Piston d'un moteur à combustion interne
CN113357628B (zh) * 2021-05-25 2024-03-19 江苏大学 一种折流式自动点火微型催化燃烧器

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US2941361A (en) * 1952-10-15 1960-06-21 Nat Res Dev Combustion apparatus having a flame stabilizing baffle
US3032991A (en) * 1959-10-01 1962-05-08 Gen Electric Combustion sustaining means for continuous flow combustion systems
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Also Published As

Publication number Publication date
JPH11507433A (ja) 1999-06-29
RU2143643C1 (ru) 1999-12-27
DE59604179D1 (de) 2000-02-17
DE19521356C2 (de) 1999-04-01
WO1996041992A1 (fr) 1996-12-27
DE19521356A1 (de) 1996-12-19
EP0832398B1 (fr) 2000-01-12
ES2142587T3 (es) 2000-04-16

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