EP0832399B1 - Catalytic ignition burner for a gas turbine - Google Patents

Catalytic ignition burner for a gas turbine 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
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EP
European Patent Office
Prior art keywords
burner
fuel
catalytic
main
gas turbine
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Revoked
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EP96917334A
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German (de)
French (fr)
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EP0832399A1 (en
Inventor
Erich Hums
Nicolas Vortmeyer
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Siemens AG
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Siemens AG
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    • 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.

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

Abstract

According to the invention a burner, especially for a gas turbine, is designed for the catalytically induced combustion of a fuel, in which the fuel outlet of a catalytic auxiliary burner (6) to stabilise the main burner (8) with the catalytic combustion of a pilot fuel flow is provided in the direction of flow of the fuel in a flow channel, in front of the fuel outlet of the main burner (8). The replacement of a diffusion pilot flame by a catalytic auxiliary burner substantially reduces the nitrogen oxide emission.

Description

Die Erfindung bezieht sich auf einen Brenner, insbesondere für eine Gasturbine, bei dem ein katalytischer Stützbrenner zur Stabilisierung eines Hauptbrenners vorgesehen ist. Derartige Brenner sind beispielsweise in Dokument EP-A-491 481 gezeigt. Als Brennstoff ist insbesondere Erdgas, Kohlegas oder ein sonstiges gasförmiges kohlenwasserstoff- und/oder wasserstoffhaltiges Gemisch vorgesehen. Ebenso eignet sich ein solches Gemisch oder ein fossiler Brennstoff in flüssiger Form.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. Such burners are shown, for example, in document EP-A-491 481. As 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.

Bei der Verbrennung eines genannten Brennstoffs entstehen als besonders unerwünschte Verbrennungsprodukte Stickoxide NOx. Diese Stickoxide gelten neben Schwefeldioxid als Hauptverursacher für das Umweltproblem des sauren Regens. Man ist daher - auch aufgrund strenger gesetzlicher Grenzwertvorgaben für den NOx-Ausstoß - gewillt, den NOx-Ausstoß eines Brenners in einer Gasturbine besonders gering zu halten, ohne dabei die Leistung des Brenners bzw. der Gasturbine wesentlich zu beeinflussen.When a named fuel is burned, 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.

So wirkt beispielsweise die Flammtemperatur-Absenkung im Brenner als stickoxidmindernd. Hierbei wird dem Brennstoff oder ebenfalls zugeführter komprimierter und vorgewärmter Frischluft Wasserdampf zugefügt oder Wasser in den Brennraum eingespritzt. Solche Maßnahmen, die den Stickoxidausstoß des Brenners per se verringern, werden als Primärmaßnaknen zur Stickoxidminderung bezeichnet.For example, 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.

Dementsprechend werden als Sekundärmaßnahmen alle Maßnahmen bezeichnet, bei denen im Abgas eines Verbrennungsprozesses enthaltene Stickoxide nachträglich verringert werden.Accordingly, all measures are considered secondary measures referred to, in which in the exhaust gas of a combustion process nitrogen oxides contained are subsequently reduced.

Hierzu hat sich weltweit das Verfahren der selektiven katalytischen Reduktion (SCR) durchgesetzt, bei dem die Stickoxide zusammen mit einem Reduktionsmittel, meist Ammoniak, an einen Katalysator kontaktiert werden und dabei Stickstoff und Wasser bilden. Mit dem Einsatz dieser Technologie ist daher zwangsläufig der Verbrauch von Reduktionsmittel verbunden. Die im Abgaskanal angeordneten Katalysatoren zur Stickoxidminderung verursachen naturgemäß einen Druckabfall in dem Abgaskanal. Ein solcher Druckabfall führt jedoch bei einem Einsatz des Brenners in einer Gasturbine zu einem beträchtlichen Leistungsabfall der Turbine. Selbst ein Leistungsabfall in Höhe von einigen Promille wirkt sich bei einer Leistung der Gasturbine von beispielsweise 150 MW und einem Stromverkaufspreis von etwa 0,15 DM/kWh Strom gravierend auf das mit einer solchen Einrichtung erzielbare Ergebnis aus.This has become the worldwide method of selective catalytic Reduction (SCR) enforced, in which the nitrogen oxides together with a reducing agent, usually ammonia Catalyst are contacted and nitrogen and water form. With the use of this technology is therefore inevitably linked to the consumption of reducing agents. The catalysts arranged in the exhaust duct for nitrogen oxide reduction naturally cause a pressure drop in the exhaust duct. However, such a drop in pressure results in use of the burner in a gas turbine to a considerable Performance loss of the turbine. Even a drop in performance The level of a few parts per thousand affects the performance of the Gas turbine of, for example, 150 MW and an electricity sales price of about 0.15 DM / kWh of electricity such an achievable result.

Neuere Überlegungen bezüglich der Ausgestaltung des Brenners gehen dahin, daß ein üblicherweise in einer Gasturbine eingesetzter Diffusionsbrenner oder drallstabilisierter Vormischbrenner durch eine katalytische Brennkammer ersetzt wird. Mit einer katalytischen Brennkammer werden niedrigere Stickoxid-Emissionen erreicht als dies mit den obengenannten Brennertypen möglich ist. Auf diese Weise können die bekannten Nachteile des SCR-Verfahrens (große Katalysatorvolumina, Reduktionsmittel-Verbrauch, hoher Druckverlust) überwunden werden.Recent considerations regarding the design of the burner go that a usually used in a gas turbine Diffusion burner or swirl-stabilized premix burner is replaced by a catalytic combustion chamber. With A catalytic combustion chamber will have lower nitrogen oxide emissions achieved than this with the above types of burners is possible. In this way, the known disadvantages the SCR process (large catalyst volumes, reducing agent consumption, high pressure loss) can be overcome.

Üblicherweise ist es zur Stabilisierung eines Brenners (Diffusionsbrenner, drallstabilisierter Vormischbrenner, katalytischer Brenner) vorgesehen, eine Pilotflamme zu verwenden. Diese Pilotflamme wird verwendet, um einen definierten Startpunkt für die Verbrennung des eigentlichen Brenngas-Hauptstroms zu setzen. Ein Brenner zur Erzeugung einer solchen Pilotflamme ist üblicherweise ein Diffusionsbrenner, der eine nicht unerhebliche Stickoxidquelle darstellt. Angesichts der durch die Stickoxide verursachten Umweltprobleme und aufgrund strenger gesetzlicher Auflagen für den Stickoxidausstoß strebt man daher an, jede auch noch so kleine Stickoxidquelle zu vermeiden oder zumindest deren Stickoxidausstoß zu verringern. It is usually used to stabilize a burner (Diffusion burner, swirl stabilized premix burner, catalytic Burner) provided to use a pilot flame. This pilot flame is used to create a defined Starting point for the combustion of the main fuel gas main stream to put. 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.

Der Erfindung liegt daher die Aufgabe zugrunde, einen Brenner, insbesondere für eine Gasturbine anzugeben, bei der die Einrichtung zur Erzeugung einer Pilotflamme besonders stickoxidarm arbeitet.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.

Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß ein Brenner zur Verbrennung eines Brennstoffes vorgesehen ist, bei dem in Strömungsrichtung des Brennstoffes in einem Strömungskanal vor dem Brennstoffauslaß eines Hauptbrenners der Brennstoffauslaß eines katalytischen Stützbrenners zur Stabilisierung des Hauptbrenners unter katalytischer Verbrennung eines Pilotbrennstoffstroms vorgesehen ist und daß bezogen auf den Querschnitt des Strömungskanals für den Brennstoff der katalytische Stützbrenner zentral und der Hauptbrenner koronal angeordnet sind. Dies ist insbesondere für eine homogene Verteilung der Pilotflamme nach radialer Richtung vorteilhaft, so daß auch die Verbrennung des Brennstoff-Hauptstromes auf einer einheitlichen Front erfolgen kann.)This object is achieved in that a Burner is provided 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.)

Der Brenner nutzt dabei eine katalytische Verbrennung des Pilotbrennstoffstroms zur Stabilisierung oder Stützung des Hauptbrenners aus.The burner uses catalytic combustion of the pilot fuel flow to stabilize or support the Main burner.

Auf diese Weise wird die zur Stabilisierung des oder der Hauptbrenner erforderliche Pilotflamme durch eine besonders stickoxidarme katalytische Verbrennung erzeugt.In this way, the stabilization of the or Main burner required pilot flame through a special Low-oxide catalytic combustion.

Für die Ausbildung der Pilotflamme ist es besonders bevorzugt, daß der Pilotbrennstoffstrom über eine Präformierungsstufe zum katalytischen Stützbrenner geführt wird. Auf diese Weise wird eine Absenkung der katalytischen Zündtemperatur des Pilotbrennstoffstromes erreicht, weil in der Präformierungsstufe der Brennstoff in leicht zündende Verbindungen zersetzt wird. Im Fall von Erdgas werden in der Präformierungsstufe beispielsweise Alkohole wie Methanol, Aldehyde und Wasserstoff gebildet.For the formation of the pilot flame, it is particularly preferred that 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. In the case of natural gas, the preforming stage for example alcohols such as methanol, aldehydes and Hydrogen formed.

Hierbei kann es weiter vorgesehen sein, daß eine Vermischung des Pilotbrennstoffstroms mit Umgebungs- und/oder Verdichterluft erfolgt. Auf diese Weise kann über die Einstellung der Volumenverhältnisse von Brennstoff/präformiertem Brennstoff zu Umgebungs- und/oder Verdichterluft der NOx-Ausstoß des Pilotbrenners weiter vermindert werden.It can further be provided that the pilot fuel flow is mixed with ambient and / or compressor air. In this way, the 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.

Zur Stabilisierung der Hauptflamme im Hauptbrenner und zur sicheren Vermeidung des Rückzündens der Hauptflamme ist es besonders bevorzugt, daß der Brennstoffauslaß des katalytischen Stützbrenners zwischen 0,5 und 5 m vor dem Brennstoffauslaß des Hauptbrenners angeordnet ist, wobei dieser Abstand vorzugsweise etwa 0,75 bis 2 m betragen kann.To stabilize the main flame in the main burner and it is sure to avoid reignition of the main flame particularly preferred that the fuel outlet of the catalytic Support burner between 0.5 and 5 m before the fuel outlet the main burner is arranged, this Distance can preferably be about 0.75 to 2 m.

In weiterer bevorzugter Ausgestaltung der Erfindung kann es vorgesehen sein, daß der Hauptbrenner als katalytischer Hauptbrenner ausgeführt ist. Ein solcher Brenner zeichnet sich ebenso wie der katalytische Stützbrenner durch vergleichsweise niedrige Stickoxid-Emissionen aus.In a further preferred embodiment of the invention, it can be provided that 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.

Ausführungsbeispiele der Erfindung werden anhand einer Zeichnung näher erläutert. Dabei zeigen:

FIG 1 und FIG 3
in schematischer Darstellung jeweils einen Längsschnitt durch den Brennerteil einer Gasturbine; und
FIG 2 und FIG 4
jeweils eine Aufsicht auf einen Querschnitt durch den Strömungskanal im Brennerteil gemäß Figur 1 bzw. Figur 3.
Embodiments of the invention are explained in more detail with reference to a drawing. Show:
1 and 3
a schematic representation of a longitudinal section through the burner part of a gas turbine; and
2 and 4
In each case a top view of a cross section through the flow channel in the burner part according to FIG. 1 or FIG. 3.

In den Figuren haben gleiche Teile gleiche Bezugszeichen. Das Ausführungsbeispiel gemäß Figuren 1 und 2 stimmt bis auf ein Merkmal überein mit dem Ausführungsbeispiel gemäß Figuren 3 und 4. Die nun folgenden Erläuterungen gelten daher sinngemäß für Figur 3 und Figur 4.In the figures, the same parts have the same reference numerals. The exemplary embodiment according to FIGS. 1 and 2 is correct except for a feature coincides with the embodiment according to figures 3 and 4. The following explanations apply accordingly for Figure 3 and Figure 4.

Figur 1 zeigt in schematischer Darstellung den Brennerteil 2 einer hier nicht weiter dargestellten Gasturbine. Der Brennerteil 2 umfaßt im Ausführungsbeispiel einen Strömungskanal 4, in den ein katalytischer Stützbrenner 6 und ein katalytischer Hauptbrenner 8 eingebaut sind. Der katalytische Stützbrenner 6 und der katalytische Hauptbrenner 8 sind rotationssymmetrisch zur Symmetrieachse 10 des Strömungskanals 4 angeordnet.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.

Durch die Anordnung des katalytischen Stützbrenners 6 zentral im Strömungskanal 4 entstehen ein äußerer Ringraum 12 und ein innerer Zentralraum 14. Im Ringraum 12 strömt ein mittels des Verdichterteils der hier nicht weiter dargestellten Gasturbine verdichtetes Brennstoffgemisch 16, bestehend aus Brenngas, hier Erdgas 18, und Luft 20. Ein in den Ringraum 12 einströmender Pilotbrennstoffstrom 22 besteht ursprünglich aus demselben Erdgas/Luft-Gasgemisch 18, 20, welches jedoch in einer Präformierungsstufe 24 präformiert wird. Der in den Stützbrenner 6 einströmende präformierte Pilotbrennstoffstrom 22 kann auch als leicht zündender Pilotbrennstoffstrom bezeichnet werden. Die Präformierung des Erdgas/Luftgemisches 18, 20 erfolgt an einem edelmetallhaltigen Katalysator, welcher beispielsweise Wabenform hat, als Hauptbestandteil Titandioxid und als katalytisch aktiven Komponenten Platin und Rhodium umfaßt. Der Katalysator ist in hier nicht weiter dargestellter Weise in der Präformierungsstufe 24 eingebaut. Optional kann dem Katalysator in der Präformierungsstufe 24 auch noch ein Wärmetauscher vorgeschaltet sein, um das in die Präformierungsstufe eintretende Erdgas/Luftgemisch 18, 20 aufzuwärmen und so die Wirksamkeit des Katalysators in der Präformierungsstufe 24 anzuheben. Bei der Präformierung bilden sich aus dem Erdgas 18 katalytisch vergleichsweise leicht zündende Stoffe, wie Methanol, Aldehyd und Wasserstoff.By arranging the catalytic auxiliary burner 6 centrally in the flow channel 4, an outer annular space 12 and a inner central space 14. In the annular space 12 flows in by means of Compressor part of the gas turbine not shown here compressed fuel mixture 16, consisting of fuel gas, here natural gas 18 and air 20. A flowing into the annular space 12 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. Optional can 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.

Im Ausführungsbeispiel ist der Brennstoffauslaß des katalytischen Stützbrenners 6 in Strömungsrichtung des Brenngases 16 in einem Abstand d von etwa 1 m vor dem Brennstoffauslaß des katalytischen Hauptbrenners 8 angeordnet. Der katalytische Stützbrenner 6 umfaßt im Ausführungsbeispiel einen Wabenkatalysator, der als Grundbestandteil mindestens eine der Substanzen Titandioxid, Siliziumdioxid und Zirkonoxid aufweist. Als katalytisch aktive Komponente sind grundsätzlich alle Edelmetalle und Metalloxide geeignet, welche eine stark oxidierende Wirkung auf die genannten Brennstoffe haben. Es sind dies beispielsweise Edelmetalle, wie Platin, Rhodium, Rhenium, Iridium, und Metalloxide, wie z. B. die Übergangsmetalloxide Vanadiumoxid, Wolframoxid, Molybdänoxid, Chromoxid, Kupferoxid, Manganoxid und Oxide der Lanthanoiden, wie z.B. Ceroxid. Ebenso können auch Metall-Ionen getauschte Zeolithe und Metalloxide vom Spinell-Typ verwendet sein.In the exemplary embodiment, 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. the 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.

Der in den katalytischen Stützbrenner 6 eintretende Pilotbrennstoffstrom 22 wird aufgrund der katalytisch aktiven Substanzen oxidiert und verbrennt mit einer Pilotflamme 26. Weil der Brennstoffauslaß des Stützbrenners 6 in Strömungsrichtung des Brenngases 16 den Abstand d vor dem Brennstoffauslaß des Hauptbrenners 8 angeordnet ist, ist es sicher gewährleistet, daß die Hauptflamme 28 nicht in den katalytischen Hauptbrenner 8 oder sogar in die Bereiche vor den katalytischen Brennern 6, 8 zurückschlagen kann. Der Abstand d beträgt im gewählten Ausführungsbeispiel etwa 1 m.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.

Das Katalysatormaterial im Hauptbrenner 8 unterscheidet sich nicht von dem Katalysatormaterial des Stützbrenners 6. Als katalytisch besonders aktive Substanz in bezug auf die Oxidation der im Brennstoff 16 enthaltenen Kohlenwasserstoffe sind jeweils 1 Gew.-% Platin und Rhodium sowie 2 Gew.-% Vanadiumoxid, Chromoxid und Wolframoxid vorgesehen. The catalyst material in the main burner 8 differs not from the catalyst material of the auxiliary burner 6. As 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.

Das aus dem Brennerteil 2 austretende Brennerabgas weist einen besonders niedrigen Stickoxidgehalt auf, weil zum einen der Brennstoff 16 im Hauptbrenner 8 katalytisch verbrannt wird, und weil die Pilotflamme 26 ebenfalls durch katalytische Verbrennung des Pilotbrennstoffstroms 22 im Stützbrenner 6 erzeugt wird. In Variation zu dem katalytischen Hauptbrenner 8 können als Hauptbrenner auch aus dem Stand der Technik bekannte Diffusionsbrenner oder drallstabilisierte Vormischbrenner verwendet sein.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. In variation to 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.

Die Figur 2 zeigt eine Aufsicht auf den Strömungskanal 4, in dem man in schematischer Darstellung die Anordnung des Hauptbrenners 8 als katalytisch aktiver Wabenkatalysator erkennt. Solche Wabenkatalysatoren haben üblicherweise eine Zellenzahl von 0,62 bis 15,5 Zellen pro cm2 (4 bis 100 Zellen pro inch2) und weisen eine Wandstärke der Stege von 0,5 bis 5 mm auf. Alternativ zu den im Ausführungsbeispiel eingesetzten Wabenkatalysatoren ist es auch möglich metallische Plattenkatalysatoren oder grundsätzlich Plattenkatalysatoren einzusetzen. Der in der Aufsicht gemäß Figur 2 zentral angeordnete katalytische Stützbrenner 6 ist bezüglich seiner Geometrie der Kanäle meist mit der Geometrie des katalytischen Hauptbrenners 8 identisch.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. Such 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. As an alternative to the honeycomb catalysts used in the exemplary embodiment, it is also possible to use 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.

Die Figuren 3 und 4 zeigen ein Ausführungsbeispiel der Erfindung, bei dem der aus Figur 1 und Figur 2 erkennbare katalytische Hauptbrenner 8 ersetzt ist durch einen nicht-katalytischen Hauptbrenner, welcher als wichtige Untercheidungsmerkmale Leitschaufeln 31 aufweist. Diese Leitschaufeln 32 prägen dem durchfließenden Brennstoff-Luft-Gemisch einen Drall auf, welcher die in diesem Gemisch einsetzende Verbrennung stabilisiert. Der nicht-katalytische Hauptbrenner ist gekennzeichnet durch einen besonders niedrigen betrieblichen Druckverlust und durch eine besondere Einfachheit des Aufbaus, was diesen Hauptbrenner zum Einsatz in einer Gasturbine besonders empfiehlt. Dadurch, daß der Hauptbrenner eine Vormischverbrennung bewirkt, ist jedenfalls ein vergleichsweise geringer NOx-Ausstoß gewährleistet. Da der Pilotbrenner 6 auch im Ausführungsbeispiel gemäß Figur 3 und Figur 4 als katalytischer Stützbrenner 6 ausgebildet ist, stellt er jedenfalls keine wesentliche Quelle für Stickoxide dar; dementsprechend ist auch der Brenner gemäß Figur 3 und Figur 4 als Brenner mit besonders geringem NOx-Ausstoß qualifiziert.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. Since 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.

Claims (7)

  1. Burner for the combustion of a fuel (16), in which the fuel outlet of a catalytic supporting burner (6) is provided in a flow duct (4), upstream of the fuel outlet of a main burner (8) in the direction of flow of the fuel (16), for the purpose of stabilizing the main burner (8), along with catalytic combustion of a pilot fuel stream (22), characterized in that the catalytic supporting burner (6) is arranged centrally and the main burner (8) is arranged coronally in relation to the cross-section of the flow duct (4) for the fuel (16).
  2. Burner according to Claim 1, characterized in that the pilot fuel stream (22) is guided to the catalytic supporting burner (6) via a preforming stage (24).
  3. Burner according to Claim 2, characterized in that a premixing of the pilot fuel stream (22) with ambient and/or compressor air (20) is provided.
  4. Burner according to one of Claims 1 to 3, characterized in that the fuel outlet of the catalytic supporting burner (6) is arranged between 0.5 and 5 m upstream of the fuel outlet of the main burner (8).
  5. Burner according to Claim 4, characterized in that the fuel outlet of the catalytic supporting burner (6) is arranged about 0.75 to 2 m upstream of the fuel outlet of the main burner (8).
  6. Burner according to one of Claims 1 to 5, characterized by a catalytic main burner (8).
  7. Gas turbine, comprising a burner according to one of Claims 1 to 6.
EP96917334A 1995-06-12 1996-06-11 Catalytic ignition burner for a gas turbine Revoked EP0832399B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19521309 1995-06-12
DE19521309 1995-06-12
PCT/DE1996/001019 WO1996041991A1 (en) 1995-06-12 1996-06-11 Catalytic ignition burner for a gas turbine

Publications (2)

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EP0832399A1 EP0832399A1 (en) 1998-04-01
EP0832399B1 true EP0832399B1 (en) 2000-01-12

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EP96917334A Revoked EP0832399B1 (en) 1995-06-12 1996-06-11 Catalytic ignition burner for a gas turbine

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JP (1) JP4063871B2 (en)
DE (1) DE59604180D1 (en)
ES (1) ES2142588T3 (en)
IN (1) IN191368B (en)
RU (1) RU2149317C1 (en)
WO (1) WO1996041991A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005054442B4 (en) * 2004-11-17 2011-04-07 Mitsubishi Heavy Industries, Ltd. Combustion chamber for a gas turbine
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 (en) * 2000-02-18 2004-07-21 日産自動車株式会社 Catalytic combustor
AU2003240374A1 (en) * 2002-08-30 2004-03-19 Alstom Technology Ltd Hybrid burner and corresponding operating method
KR101974819B1 (en) * 2011-08-17 2019-08-23 다이요 닛산 가부시키가이샤 H2 burner and h2 burner combustion method
US9322557B2 (en) * 2012-01-05 2016-04-26 General Electric Company Combustor and method for distributing fuel in the combustor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5963407A (en) * 1982-10-01 1984-04-11 Matsushita Electric Ind Co Ltd Catalitic burner
JPS61276627A (en) * 1985-05-30 1986-12-06 Toshiba Corp Gas turbine combustion apparatus
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 (en) * 2004-11-17 2011-04-07 Mitsubishi Heavy Industries, Ltd. Combustion chamber for a gas turbine

Also Published As

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WO1996041991A1 (en) 1996-12-27
RU2149317C1 (en) 2000-05-20
JPH11509307A (en) 1999-08-17
EP0832399A1 (en) 1998-04-01
DE59604180D1 (en) 2000-02-17
ES2142588T3 (en) 2000-04-16
IN191368B (en) 2003-11-29
JP4063871B2 (en) 2008-03-19

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