EP0832399A1 - Catalytic ignition burner for a gas turbine - Google Patents

Catalytic ignition burner for a gas turbine

Info

Publication number
EP0832399A1
EP0832399A1 EP96917334A EP96917334A EP0832399A1 EP 0832399 A1 EP0832399 A1 EP 0832399A1 EP 96917334 A EP96917334 A EP 96917334A EP 96917334 A EP96917334 A EP 96917334A EP 0832399 A1 EP0832399 A1 EP 0832399A1
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.)
Granted
Application number
EP96917334A
Other languages
German (de)
French (fr)
Other versions
EP0832399B1 (en
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
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
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Application filed by Siemens AG filed Critical Siemens AG
Publication of EP0832399A1 publication Critical patent/EP0832399A1/en
Application granted granted Critical
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Anticipated expiration legal-status Critical
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Links

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 for stabilizing a main burner.
  • Natural gas, coal gas or some other gaseous hydrocarbon and / or hydrogen-containing mixture is provided as the fuel.
  • Such a mixture or a fossil fuel in liquid form are also suitable.
  • 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.
  • reducing the flame temperature in the burner reduces nitrogen oxide.
  • water vapor is added to the fuel or compressed and preheated fresh air, or water is injected into the combustion chamber.
  • Measures that reduce the burner's nitrogen oxide emissions per se are referred to as primary measures for nitrogen oxide reduction.
  • a burner for generating such a pilot flame is usually a diffusion burner, which is a not insignificant source of nitrogen oxide.
  • the aim is therefore to avoid any source of nitrogen oxide, however small, or at least to reduce its nitrogen oxide emission.
  • the invention is therefore based on the object of specifying a burner, in particular for a gas turbine, in which the device for generating a pilot flame works particularly low in nitrogen oxide.
  • a burner is provided for the combustion of a fuel, in which the fuel outlet of a catalytic auxiliary burner for stabilizing the main burner with catalytic combustion of a pilot fuel flow is provided in a flow channel in the flow direction of the fuel in a flow channel is.
  • the burner uses a catalytic combustion of the pilot fuel flow to stabilize or support the main burner.
  • the pilot flame required to stabilize the main burner or burners is generated by a catalytic combustion which is particularly low in nitrogen oxide.
  • the catalytic auxiliary burner is central and the
  • Main burners are arranged coronally. This is particularly advantageous for a homogeneous distribution of the pilot flame in the radial direction, so that the combustion of the main fuel stream can also take place on a uniform front.
  • the pilot fuel flow is led to the catalytic auxiliary burner via a preforming stage.
  • a lowering of the catalytic ignition temperature of the pilot fuel flow is achieved, because in the preforming stage the fuel turns into easily igniting compounds is decomposed.
  • alcohols such as methanol, aldehydes and hydrogen are formed in the preforming stage, for example.
  • pilot fuel stream 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.
  • the fuel outlet of the catalytic auxiliary burner is arranged between 0.5 and 5 m in front of the fuel outlet of the main burner, this distance preferably being about 0 , Can be 75 to 2 m.
  • the main burner is designed as a catalytic main burner.
  • a burner like the catalytic auxiliary burner, is distinguished by comparatively low nitrogen oxide emissions.
  • FIG. 2 and 4 each show a top view of a cross section through the flow channel in the burner part according to FIG. 1 and FIG. 3.
  • FIGS. 1 and 2 coincides with one feature with the exemplary embodiment according to FIGS. 3 and 4.
  • the explanations which now follow therefore apply mutatis mutandis to FIGS. 3 and 4.
  • FIG. 1 shows a schematic representation of the burner part 2 of a gas turbine not shown here.
  • the burner part 2 comprises a flow channel 4, into which a catalytic auxiliary burner 6 and a catalytic main burner 8 are installed.
  • the catalytic support burner 6 and the main catalytic burner 8 are arranged rotationally symmetrically to the axis of symmetry 10 of the flow channel 4.
  • the arrangement of the catalytic auxiliary burner 6 in the center of the flow channel 4 creates an outer annular space 12 and an inner central space 14.
  • a fuel mixture 16, consisting of fuel gas, here natural gas, is compressed in the annular space 12 by means of the compressor part of the gas turbine (not shown here) 18, and air 20.
  • a pilot fuel flow 22 flowing into the annular space 12 originally consists of the same natural gas / air-gas mixture 18, 20 which, however, is preformed in a preforming stage 24.
  • the preformed pilot fuel flow 22 flowing into the support burner 6 can also be referred to as an easily igniting pilot fuel flow.
  • the natural gas / air mixture 18, 20 is preformed on a noble metal-containing catalyst which, for example, has a honeycomb shape, comprises titanium dioxide as the main component and platinum and rhodium as the catalytically active components.
  • the catalyst is installed in the preforming stage 24 in a manner not shown here.
  • a heat exchanger can also be connected upstream of the catalyst in the preforming stage 24 in order to warm up the natural gas / air mixture 18, 20 entering the preforming stage and thus the effectiveness of the catalyst in the
  • the fuel outlet of the catalytic auxiliary burner 6 is arranged in the flow direction of the fuel gas 16 at a distance d of approximately 1 m in front of the fuel outlet of the main catalytic burner 8.
  • the catalytic auxiliary burner 6 comprises a honeycomb catalyst which has at least one of the substances titanium dioxide, silicon dioxide and zirconium oxide as the basic constituent.
  • all noble metals and metal oxides which have a strongly oxidizing effect on the fuels mentioned are suitable as catalytically active components. These are, for example, noble 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 lanthanides, such as e.g. Cerium oxide.
  • Metal ion exchanged zeolites and metal oxides of the spinel type can also be used.
  • the pilot fuel flow 22 entering the catalytic auxiliary burner 6 is oxidized due to the catalytically active substances and burns with a pilot flame 26. Because the fuel outlet of the auxiliary burner 6 is arranged in the flow direction of the fuel gas 16 the distance d in front of the fuel outlet of the main burner 8, it is guaranteed that the main flame 28 cannot strike back into the main catalytic burner 8 or even into the areas in front of the catalytic burner 6, 8.
  • the distance d is approximately 1 m in the selected exemplary embodiment.
  • the catalyst material in the main burner 8 does not differ from the catalyst material of the auxiliary burner 6.
  • a catalytically particularly active substance with regard to the oxidation of the hydrocarbons contained in the fuel 1% by weight of platinum and rhodium and 2% by weight of vanadium are in each case ⁇ oxide, chromium oxide and tungsten oxide provided.
  • the burner exhaust gas emerging from the burner part 2 has a particularly low nitrogen oxide content because, on the one hand, the fuel 16 is burned catalytically in the main burner 8 and because the pilot flame 26 is also generated by catalytic combustion of the pilot fuel stream 22 in the auxiliary burner 6.
  • diffusion burners or spin-stabilized premix burners known from the prior art can also be used as main burners.
  • 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 number of 4 to 100 cells per inch ⁇ and have a wall thickness of the webs of 0.5 to 5 mm.
  • metallic plate catalysts or, in principle, plate catalysts.
  • the catalytic auxiliary burner 6 arranged centrally in the top view according to FIG. 2 is usually identical to the geometry of the catalytic main burner 8.
  • 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 31 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 drop and by a particular simplicity of construction, which particularly recommends this main burner for use in a gas turbine. In any case, the fact that the main burner causes premix combustion is a comparatively small one NO x emissions guaranteed.
  • 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.

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

Beschreibungdescription
KATALITISCHE ZÜNDBRENNER EINER GASTURBINECATALITIC BURNER OF A GAS TURBINE
Die Erfindung bezieht sich auf einen Brenner, insbesondere für eine Gasturbine, bei dem ein katalytischer Stützbrenner zur Stabilisierung eines Hauptbrenners vorgesehen ist. Als Brennstoff ist insbesondere Erdgas, Kohlegas oder ein sonsti- ges gasförmiges kohlenwasserstoff- und/oder wasserstoffhalti- ges Gemisch vorgesehen. Ebenso eignet sich ein solches Ge¬ misch 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 for stabilizing a main burner. Natural gas, coal gas or some other gaseous hydrocarbon and / or hydrogen-containing mixture is provided as the fuel. Such a mixture or a fossil fuel in liquid form are also suitable.
Bei der Verbrennung eines genannten Brennstoffs entstehen als besonders unerwünschte Verbrennungsprodukte Stickoxide NOx. Diese Stickoxide gelten neben Schwefeldioxid als Hauptverur- sacher 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 be¬ einflussen.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 Waεserdampf zugefügt oder Wasser in den Brennraum eingespritzt. Solche Maßnahmen, die den Stickoxidausstoß des Brenners per se verringern, werden als Primärmaßnahmen zur Stickoxidminderung bezeichnet.For example, reducing the flame temperature in the burner reduces nitrogen oxide. In this case, water vapor is added to the fuel or compressed and preheated fresh air, or water is injected into the combustion chamber. Measures that reduce the burner's nitrogen oxide emissions per se are referred to as primary measures for 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 referred to as secondary measures in which nitrogen oxides contained in the exhaust gas of a combustion process are subsequently reduced.
Hierzu hat sich weltweit das Verfahren der selektiven kataly¬ tischen Reduktion (SCR) durchgesetzt, bei dem die Stickoxide zusammen mit einem Reduktionsmittel, meist Ammoniak, an einen Katalysator kontaktiert werden und dabei Stickstoff und Was¬ ser bilden. Mit dem Einsatz dieser Technologie ist daher zwangsläufig der Verbrauch von Reduktionsmittel verbunden. Die im Abgaskanal angeordneten Katalysatoren zur Stickoxid¬ minderung verursachen naturgemäß einen Druckabfall in dem Ab¬ gaskanal. Ein solcher Druckabfall führt jedoch bei einem Ein¬ satz 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 Stromver¬ kaufspreis von etwa 0,15 DM/kWh Strom gravierend auf das mit einer solchen Einrichtung erzielbare Ergebnis aus.For this purpose, the process of selective catalytic reduction (SCR) has established itself worldwide, in which the nitrogen oxides are contacted with a reducing agent, usually ammonia, on a catalyst and thereby form nitrogen and water. The use of this technology therefore inevitably involves the consumption of reducing agents. The catalysts for reducing nitrogen oxide arranged in the exhaust gas channel naturally cause a pressure drop in the exhaust gas channel. However, such a drop in pressure leads to a considerable drop in the power of the turbine when the burner is used in a gas turbine. Even a drop in output in the amount of a few per thousand, with an output of the gas turbine of, for example, 150 MW and an electricity sales price of approximately 0.15 DM / kWh of electricity, has a serious effect on the result which can be achieved with such a device.
Neuere Überlegungen bezüglich der Ausgestaltung des Brenners gehen dahin, daß ein üblicherweise in einer Gasturbine einge¬ setzter Diffusionsbrenner oder drallstabilisierter Vormisch- brenner durch eine katalytische Brennkammer ersetzt wird. Mit einer katalytischen Brennkammer werden niedrigere Stickoxid- Emissionen erreicht als dies mit den obengenannten Brennerty¬ pen möglich ist. Auf diese Weise können die bekannten Nach¬ teile des SCR-Verfahrens (große Katalysatorvolumina, Redukti¬ onsmittel-Verbrauch, hoher Druckverlust) überwunden werden.More recent considerations regarding the design of the burner are that a diffusion burner or swirl-stabilized premix burner, which is usually used in a gas turbine, is replaced by a catalytic combustion chamber. With a catalytic combustion chamber, lower nitrogen oxide emissions are achieved than is possible with the above-mentioned burner types. In this way, the known disadvantages of the SCR process (large catalyst volumes, reducing agent consumption, high pressure loss) can be overcome.
Üblicherweise ist es zur Stabilisierung eines BrennersIt is usually used to stabilize a burner
(Diffusionsbrenner, drallstabilisierter Vormischbrenner, ka¬ talytischer Brenner) vorgesehen, eine Pilotflamme zu verwen¬ den. Diese Pilotflamme wird verwendet, um einen definierten Startpunkt für die Verbrennung des eigentlichen Brenngas- Hauptstroms zu setzen. Ein Brenner zur Erzeugung einer sol¬ chen Pilotflamme ist üblicherweise ein Diffusionsbrenner, der eine nicht unerhebliche Stickoxidquelle darstellt. Angesichts der durch die Stickoxide verursachten Umweltprobleme und auf¬ grund strenger gesetzlicher Auflagen für den Stickoxidausstoß strebt man daher an, jede auch noch so kleine Stickoxidquelle zu vermeiden oder zumindest deren Stickoxidausstoß zu verrin¬ gern. Der Erfindung liegt daher die Aufgabe zugrunde, einen Bren¬ ner, insbesondere für eine Gasturbine anzugeben, bei der die Einrichtung zur Erzeugung einer Pilotflamme besonders stick- oxidarm arbeitet.(Diffusion burner, swirl-stabilized premix burner, catalytic burner) provided to use a pilot flame. This pilot flame is used to set a defined starting point for the combustion of the actual main fuel gas stream. A burner for generating such a pilot flame is usually a diffusion burner, which is a not insignificant source of nitrogen oxide. In view of the environmental problems caused by the nitrogen oxides and due to strict legal requirements for nitrogen oxide emissions, the aim is therefore to avoid any source of nitrogen oxide, however small, or at least to reduce its nitrogen oxide emission. The invention is therefore based on the object of specifying a burner, in particular for a gas turbine, in which the device for generating a pilot flame works particularly low in nitrogen oxide.
Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß ein Brenner zur Verbrennung eines Brennstoffes vorgesehen ist, bei dem in Strömungsrichtung des Brennstoffes in einem Strö- mungskanal vor dem Brennstoffauslaß eines Hauptbrenners der Brennstoffauslaß eines katalytischen Stützbrenners zur Stabi¬ lisierung des Hauptbrenners unter katalytischer Verbrennung eines Pilotbrennstoffstroms vorgesehen ist.This object is achieved according to the invention in that a burner is provided for the combustion of a fuel, in which the fuel outlet of a catalytic auxiliary burner for stabilizing the main burner with catalytic combustion of a pilot fuel flow is provided in a flow channel in the flow direction of the fuel in a flow channel is.
Der Brenner nutzt dabei eine katalytische Verbrennung des Pi¬ lotbrennstoffStroms zur Stabilisierung oder Stützung des Hauptbrenners aus.The burner uses a 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 pilot flame required to stabilize the main burner or burners is generated by a catalytic combustion which is particularly low in nitrogen oxide.
In bevorzugter Ausgestaltung der Erfindung kann es vorgesehen sein, daß bezogen auf den Querschnitt des Strömungskanals für den Brennstoff der katalytische Stützbrenner zentral und derIn a preferred embodiment of the invention, it can be provided that, based on the cross section of the flow channel for the fuel, the catalytic auxiliary burner is central and the
Hauptbrenner koronal angeordnet sind. Dies ist insbesondere für eine homogene Verteilung der Pilotflamme nach radialer Richtung vorteilhaft, so daß auch die Verbrennung des Erenn- stoff-Hauptstromeε auf einer einheitlichen Front erfolgen kann.Main burners are arranged coronally. This is particularly advantageous for a homogeneous distribution of the pilot flame in the radial direction, so that the combustion of the main fuel stream can also take place on a uniform front.
Für die Ausbildung der Pilotflamme ist es besonders bevor¬ zugt, daß der Pilotbrennstoffström über eine Präformierungs¬ stufe zum katalytischen Stützbrenner geführt wird. Auf diese Weise wird eine Absenkung der katalytischen Zündtemperatur des PilotbrennstoffStromes erreicht, weil in der Präformie¬ rungsstufe der Brennstoff in leicht zündende Verbindungen zersetzt wird. Im Fall von Erdgas werden in der Präformie¬ rungsstufe beispielsweise Alkohole wie Methanol, Aldehyde und Wasserstoff gebildet.For the formation of the pilot flame, it is particularly preferred that the pilot fuel flow is led to the catalytic auxiliary burner via a preforming stage. In this way, a lowering of the catalytic ignition temperature of the pilot fuel flow is achieved, because in the preforming stage the fuel turns into easily igniting compounds is decomposed. In the case of natural gas, alcohols such as methanol, aldehydes and hydrogen are formed in the preforming stage, for example.
Hierbei kann es weiter vorgesehen sein, daß eine Vermischung des PilotbrennstoffStroms mit Umgebungs- und/oder Verdichter¬ luft erfolgt. Auf diese Weise kann über die Einstellung der Volumenverhältnisse von Brennstoff/präformiertem Brennstoff zu Umgebungs- und/oder Verdichterluft der NOx-Ausstoß des Pi- lotbrenners weiter vermindert werden.It can further be provided that the pilot fuel stream 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 katalyti- sehen Stützbrenners zwischen 0,5 und 5 m vor dem Brenn¬ stoffauslaß 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 to reliably prevent the main flame from reigniting, it is particularly preferred that the fuel outlet of the catalytic auxiliary burner is arranged between 0.5 and 5 m in front of the fuel outlet of the main burner, this distance preferably being about 0 , Can be 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 ver¬ gleichsweise niedrige Stickoxid-Emissionen aus.In a further preferred embodiment of the invention it can be provided that the main burner is designed as a catalytic main burner. Such a burner, like the catalytic auxiliary burner, is distinguished by comparatively low nitrogen oxide emissions.
Ausführungsbeispiele der Erfindung werden anhand einer Zeich¬ nung näher erläutert. Dabei zeigen:Embodiments of the invention are explained in more detail with reference to a drawing. Show:
FIG 1 und FIG 3 in schematischer Darstellung jeweils ei¬ nen Längsschnitt durch den Brennerteil einer Gastur- bine; und1 and 3 each show a schematic representation of a longitudinal section through the burner part of a gas turbine; and
FIG 2 und FIG 4 jeweils eine Aufsicht auf einen Quer¬ schnitt durch den Strömungskanal im Brennerteil gemäß Figur 1 bzw. Figur 3.2 and 4 each show a top view of a cross section through the flow channel in the burner part according to FIG. 1 and 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 sinnge¬ mäß 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 coincides with one feature with the exemplary embodiment according to FIGS. 3 and 4. The explanations which now follow therefore apply mutatis mutandis to FIGS. 3 and 4.
Figur 1 zeigt in schematischer Darstellung den Brennerteil 2 einer hier nicht weiter dargestellten Gasturbine. Der Bren¬ nerteil 2 umfaßt im Ausführungsbeispiel einen Strömungskanal 4, in den ein katalytischer Stützbrenner 6 und ein katalyti- scher Hauptbrenner 8 eingebaut sind. Der katalytische Stütz¬ brenner 6 und der katalytische Hauptbrenner 8 sind rotations¬ symmetrisch zur Symmetrieachse 10 des Strömungskanals 4 ange¬ ordnet.Figure 1 shows a schematic representation of the burner part 2 of a gas turbine not shown here. In the exemplary embodiment, the burner part 2 comprises a flow channel 4, into which a catalytic auxiliary burner 6 and a catalytic main burner 8 are installed. The catalytic support burner 6 and the main catalytic burner 8 are arranged rotationally symmetrically 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 ströme ein mitteis des Verdichterteils der hier nicht weiter dargestellten Gastur¬ bine verdichtetes Brennstoffgemisch 16, bestehend aus Brenn- gas, hier Erdgas 18, und Luft 20. Ein in den Ringraum 12 ein¬ strömender Pilotbrennstoffström 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 Pilotbrennεtoffström 22 kann auch als leicht zündender Pilotbrennstoffström be¬ zeichnet werden. Die Präformierung des Erdgas/Luftgemiεehes 18, 20 erfolgt an einem edelmetallhaltigen Katalysator, wel¬ cher beispielsweise Wabenform hat, als Hauptbestandteil Ti¬ tandioxid und als katalytisch aktiven Komponenten Platin und Rhodium umfaßt. Der Katalysator ist in hier nicht weiter dar¬ gestellter Weise in der Präformierungsstufe 24 eingebaut. Op¬ tional 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 derThe arrangement of the catalytic auxiliary burner 6 in the center of the flow channel 4 creates an outer annular space 12 and an inner central space 14. A fuel mixture 16, consisting of fuel gas, here natural gas, is compressed in the annular space 12 by means of the compressor part of the gas turbine (not shown here) 18, and air 20. A pilot fuel flow 22 flowing into the annular space 12 originally consists of the same natural gas / air-gas mixture 18, 20 which, however, is preformed in a preforming stage 24. The preformed pilot fuel flow 22 flowing into the support burner 6 can also be referred to as an easily igniting pilot fuel flow. The natural gas / air mixture 18, 20 is preformed on a noble metal-containing catalyst which, for example, has a honeycomb shape, comprises titanium dioxide as the main component and platinum and rhodium as the catalytically active components. The catalyst is installed in the preforming stage 24 in a manner not shown here. Optionally, a heat exchanger can also be connected upstream of the catalyst in the preforming stage 24 in order to warm up the natural gas / air mixture 18, 20 entering the preforming stage and thus the effectiveness of the catalyst in the
Präformierungsstufe 24 anzuheben. Bei der Präformierung bil- den sich aus dem Erdgas 18 katalytisch vergleichsweise leicht zündende Stoffe, wie Methanol, Aldehyd und Wasserstoff.Raise preformation level 24. When preforming, the substances which ignite comparatively easily from the natural gas 18, such as methanol, aldehyde and hydrogen.
Im Ausführungsbeispiel ist der Brennstoffauslaß des katalyti- sehen 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 Wabenkata¬ lysator, der als Grundbestandteil mindestens eine der Sub- stanzen Titandioxid, Siliziumdioxid und Zirkonoxid aufweist. Als katalytisch aktive Komponente sind grundsätzlich alle Edelmetalle und Metalloxide geeignet, welche eine stark oxi- dierende Wirkung auf die genannten Brennstoffe haben. Es sind dies beispielsweise Edelmetalle, wie Platin, Rhodium, Rhe- nium, Iridium, und Metalloxide, wie z. B. die Übergangsme¬ talloxide 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 of the catalytic auxiliary burner 6 is arranged in the flow direction of the fuel gas 16 at a distance d of approximately 1 m in front of the fuel outlet of the main catalytic burner 8. In the exemplary embodiment, the catalytic auxiliary burner 6 comprises a honeycomb catalyst which has at least one of the substances titanium dioxide, silicon dioxide and zirconium oxide as the basic constituent. In principle, all noble metals and metal oxides which have a strongly oxidizing effect on the fuels mentioned are suitable as catalytically active components. These are, for example, noble 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 lanthanides, such as e.g. Cerium oxide. Metal ion exchanged zeolites and metal oxides of the spinel type can also be used.
Der in den katalytischen Stützbrenner 6 eintretende Pilot¬ brennstoffström 22 wird aufgrund der katalytisch aktiven Sub¬ stanzen 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 Hauptbren¬ ner 8 oder sogar in die Bereiche vor den katalytischen Bren¬ nern 6, 8 zurückschlagen kann. Der Abstand d beträgt im ge- wählten Ausführungsbeispiel etwa 1 m.The pilot fuel flow 22 entering the catalytic auxiliary burner 6 is oxidized due to the catalytically active substances and burns with a pilot flame 26. Because the fuel outlet of the auxiliary burner 6 is arranged in the flow direction of the fuel gas 16 the distance d in front of the fuel outlet of the main burner 8, it is guaranteed that the main flame 28 cannot strike back into the main catalytic burner 8 or even into the areas in front of the catalytic burner 6, 8. The distance d is approximately 1 m in the selected exemplary embodiment.
Das Katalysatormaterial im Hauptbrenner 8 unterscheidet sich nicht von dem Katalysatormaterial des Stützbrenners 6. Als katalytisch besonders aktive Substanz in bezug auf die Oxida- tion der im Brennstoff 16 enthaltenen Kohlenwasserstoffe sind jeweils 1 Gew.-% Platin und Rhodium sowie 2 Gew.-% Vanadium¬ oxid, Chromoxid und Wolframoxid vorgesehen. Das aus dem Brennerteil 2 austretende Brennerabgas weist ei¬ nen besonders niedrigen Stickoxidgehalt auf, weil zum einen der Brennstoff 16 im Hauptbrenner 8 katalytisch verbrannt wird, und weil die Pilotflamme 26 ebenfalls durch katalyti¬ sche Verbrennung des PilotbrennstoffStroms 22 im Stützbrenner 6 erzeugt wird. In Variation zu dem katalytischen Hauptbren¬ ner 8 können als Hauptbrenner auch aus dem Stand der Technik bekannte Diffusionsbrenner oder drallstabilisierte Vormisch- brenner verwendet sein.The catalyst material in the main burner 8 does not differ from the catalyst material of the auxiliary burner 6. As a catalytically particularly active substance with regard to the oxidation of the hydrocarbons contained in the fuel 16, 1% by weight of platinum and rhodium and 2% by weight of vanadium are in each case ¬ oxide, chromium oxide and tungsten oxide provided. The burner exhaust gas emerging from the burner part 2 has a particularly low nitrogen oxide content because, on the one hand, the fuel 16 is burned catalytically in the main burner 8 and because the pilot flame 26 is also generated by catalytic combustion of the pilot fuel stream 22 in the auxiliary burner 6. In a variation of the main catalytic burner 8, diffusion burners or spin-stabilized premix burners known from the prior art can also be used as main burners.
Die Figur 2 zeigt eine Aufsicht auf den Strömungskanal 4, in dem man in schematischer Darstellung die Anordnung des Haupt¬ brenners 8 als katalytisch aktiver Wabenkatalysator erkennt. Solche Wabenkatalysatoren haben üblicherweise eine Zellenzahl von 4 bis 100 Zellen pro inch^ und weisen eine Wandstärke der Stege von 0,5 bis 5 mm auf. Alternativ zu den im Ausführungs- beispiel eingesetzten Wabenkatalysatoren ist es auch möglich metallische Plattenkatalysatoren oder grundsätzlich Platten- katalyεatoren einzusetzen. Der in der Aufsicht gemäß Figur 2 zentral angeordnete katalytische Stützbrenner 6 ist bezüglich seiner Geometrie der Kanäle meist mit der Geometrie des kata¬ lytischen 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 number of 4 to 100 cells per inch ^ 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. In terms of the geometry of the channels, the catalytic auxiliary burner 6 arranged centrally in the top view according to FIG. 2 is usually identical to the geometry of the catalytic main burner 8.
Die Figuren 3 und 4 zeigen ein Ausführungsbeispiel der Erfin¬ dung, bei dem der aus Figur 1 und Figur 2 erkennbare kataly¬ tische Hauptbrenner 8 ersetzt ist durch einen nicht-kacalyti- schen Hauptbrenner, welcher als wichtige Unterscheidungsmerk¬ male Leitschaufeln 31 aufweist. Diese Leitschaufeln 31 prägen dem durchfließenden Brennstoff-Luft-Gemisch einen Drall auf, welcher die in diesem Gemisch einsetzende Verbrennung stabi¬ lisiert. Der nicht-katalytische Hauptbrenner ist gekennzeich¬ net durch einen besonders niedrigen betrieblichen Druckver¬ lust und durch eine besondere Einfachheit des Aufbaus, was diesen Hauptbrenner zum Einsatz in einer Gasturbine besonders empfiehlt. Dadurch, daß der Hauptbrenner eine Vormiεchver- brennung bewirkt, ist jedenfalls ein vergleichsweise geringer NOx-Ausstoß gewährleistet. Da der Pilotbrenner 6 auch im Aus- führungsbeispiel 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 31 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 drop and by a particular simplicity of construction, which particularly recommends this main burner for use in a gas turbine. In any case, the fact that the main burner causes premix combustion is a comparatively small one NO x emissions guaranteed. 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

Patentansprüche claims
1. Brenner zur Verbrennung eines Brennstoffes (16), bei dem in Strömungsrichtung des Brennstoffes (16) in einem Strö¬ mungskanal (4) vor dem Brennstoffauslaß eines Hauptbrenners (8) der Brennstoffauslaß eines katalytischen Stützbrenners (6) zur Stabilisierung des Hauptbrenners (8) unter katalyti¬ scher Verbrennung eines PilotbrennstoffStroms (22) vorgesehen ist.1. Burner for the combustion of a fuel (16), in which the fuel outlet of a catalytic auxiliary burner (6) for stabilizing the main burner (8) in a flow channel (4) in the flow direction of the fuel (16) in front of the fuel outlet of a main burner (8) ) is provided with catalytic combustion of a pilot fuel stream (22).
2. Brenner nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, daß bezogen auf den Querschnitt des Strömungskanals (4) für den Brenn¬ stoff (16) der katalytische Stützbrenner (6) zentral und der Hauptbrenner (8) koronal angeordnet sind.2. Burner according to claim 1, d a d u r c h g e k e n n z e i c h n e t that based on the cross section of the flow channel (4) for the Brenn¬ fuel (16) the catalytic support burner (6) centrally and the main burner (8) are arranged coronally.
3. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, daß der Pilot¬ brennstoffström (22) über eine Präformierungsstufe (24) zum katalytischen Stützbrenner (6) geführt ist.3. Burner according to claim 1 or 2, so that the pilot fuel flow (22) is guided via a preforming stage (24) to the catalytic auxiliary burner (6).
4. Brenner nach Anspruch 3, d a d u r c h g e k e n n z e i c h n e t, daß eine Vor¬ mischung des PilotbrennstoffStroms (22) mit Umgebungs- und/oder Verdichterluft (20) vorgesehen ist.4. Burner according to claim 3, so that a premixing of the pilot fuel stream (22) with ambient and / or compressor air (20) is provided.
5. Brenner nach einem der Ansprüche 1 bis 4, d a d u r c h g e k e n n z e i c h n e t, daß der Brenn¬ stoffauslaß des katalytischen Stützbrenners (6) zwischen 0,5 und 5 m vor dem Brennstoffauslaß des Hauptbrenners (8) ange¬ ordnet ist.5. Burner according to one of claims 1 to 4, so that the fuel outlet of the catalytic auxiliary burner (6) is arranged between 0.5 and 5 m in front of the fuel outlet of the main burner (8).
6. Brenner nach Anspruch 5, d a d u r c h g e k e n n z e i c h n e t, daß der Brenn- stoffauslaß des katalytischen Stützbrenners (6) etwa 0,75 bis 2 m vor dem Brennstoffauslaß des Hauptbrenners (8) angeordnet ist. 6. Burner according to claim 5, characterized in that the fuel outlet of the catalytic auxiliary burner (6) is arranged about 0.75 to 2 m before the fuel outlet of the main burner (8).
7. Brenner nach einem der Ansprüche 1 bis 6, g e k e n n z e i c h n e t d u r c h einen katalytischen Hauptbrenner (8) .7. Burner according to one of claims 1 to 6, g e k e n n z e i c h n e t d u r c h a main catalytic burner (8).
8. Gasturbine umfassend einen Brenner nach einem der Ansprü¬ che 1 bis 7. 8. Gas turbine comprising a burner according to one of claims 1 to 7.
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)

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

Family

ID=7764161

Family Applications (1)

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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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EP (1) EP0832399B1 (en)
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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1510761A1 (en) * 2003-08-13 2005-03-02 Siemens Aktiengesellschaft Method for burning a fluid fuel as well as burner, in particular for a gas turbine, for carrying out the method

Families Citing this family (5)

* 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
EP1532394B1 (en) 2002-08-30 2016-11-23 General Electric Technology GmbH Hybrid burner and corresponding operating method
JP4015656B2 (en) * 2004-11-17 2007-11-28 三菱重工業株式会社 Gas turbine combustor
JP5732135B2 (en) * 2011-08-17 2015-06-10 大陽日酸株式会社 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9641991A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1510761A1 (en) * 2003-08-13 2005-03-02 Siemens Aktiengesellschaft Method for burning a fluid fuel as well as burner, in particular for a gas turbine, for carrying out the method
WO2005019734A1 (en) * 2003-08-13 2005-03-03 Siemens Aktiengesellschaft Method for the combustion of a fluid fuel, and burner, especially of a gas turbine, for carrying out said method

Also Published As

Publication number Publication date
DE59604180D1 (en) 2000-02-17
IN191368B (en) 2003-11-29
RU2149317C1 (en) 2000-05-20
JP4063871B2 (en) 2008-03-19
WO1996041991A1 (en) 1996-12-27
JPH11509307A (en) 1999-08-17
EP0832399B1 (en) 2000-01-12
ES2142588T3 (en) 2000-04-16

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