EP2151630A1 - Swirler and swirler assembly - Google Patents

Swirler and swirler assembly Download PDF

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Publication number
EP2151630A1
EP2151630A1 EP08013950A EP08013950A EP2151630A1 EP 2151630 A1 EP2151630 A1 EP 2151630A1 EP 08013950 A EP08013950 A EP 08013950A EP 08013950 A EP08013950 A EP 08013950A EP 2151630 A1 EP2151630 A1 EP 2151630A1
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EP
European Patent Office
Prior art keywords
swirler
hub
boundary wall
fuel
pilot
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
EP08013950A
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German (de)
French (fr)
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EP2151630B1 (en
Inventor
Marcus Fischer
Michael Dr. Huth
Bernd Dr. Prade
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
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Siemens AG
Siemens Corp
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Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP08013950A priority Critical patent/EP2151630B1/en
Priority to AT08013950T priority patent/ATE528589T1/en
Priority to JP2009179079A priority patent/JP5574635B2/en
Publication of EP2151630A1 publication Critical patent/EP2151630A1/en
Application granted granted Critical
Publication of EP2151630B1 publication Critical patent/EP2151630B1/en
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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes

Definitions

  • Gas turbines are known to have the following components: a compressor for compressing air; at least one combustion chamber for generating hot gas by burning fuel in the presence of the compressed air supplied by the compressor; and a turbine in which the hot gas supplied from the combustion chamber is expanded.
  • NOx nitrogen oxides
  • CO carbon monoxide
  • One known factor affecting NOx emissions is the combustion temperature. If the combustion temperature is lowered, the amount of NOx released decreases. However, high combustion temperatures are desirable to achieve high efficiency and enhance CO oxidation. It is known that leaner fuel / air mixtures burn cooler and therefore less NOx emissions arise.
  • One known technique for producing a leaner fuel mixture is to create turbulence to mix air and fuel as evenly as possible prior to combustion to avoid creating zones of rich mixture in which there are high temperature localities called hot spots).
  • combustion engines in particular those which are operated with two different fuels, for example, an injection of the fuel oil via Swirler, in which the oil is mixed with air.
  • Swirler in which the oil is mixed with air.
  • These swirlers are usually arranged concentrically around a heavily twisted pilot burner. The pilot is followed by a pilot cone, in which the pilot gas combustion takes place. This, downstream in the flow direction, the main combustion takes place. Combustion air flows through the pilot or the Swirler and is mixed there with fuel. To prevent unwanted ignition of the mixture, the intermediate areas between the swirlers are traversed by air or an air / fuel mixture. This air is available for an improvement of the mixture and / or for a reduction of the maximum combustion temperature only limited.
  • the U 6,038,861 discloses a Swirler, which have a round cross-section at the combustion air inlet side. These expand with increasing flow direction. Adjacent swirlers eventually join together to form an annular gap. However, this is difficult to implement on the production side.
  • a first object of the present invention to provide a swirler which overcomes the above disadvantages.
  • a second object of the present invention is to disclose an advantageous swirler arrangement.
  • Another object of the invention is to provide an advantageous burner.
  • the object is achieved by the specification of a swirler according to claim 1.
  • the further object is achieved by the specification of a swirler arrangement according to claim 8.
  • the object related to the burner is achieved by the specification of a burner according to claim 10.
  • a swirler with a hub arranged along an axis (A) and with a boundary wall (B) completely surrounding the hub, said swirler comprising at least one swirl blade directed radially outwards from the hub extends to the boundary wall (B).
  • the cross section formed by the boundary wall (B) perpendicular to the axis (A) is trapezoidal.
  • the invention has thus recognized that in the current geometry of the Swirler an intensive flow through the intermediate areas with air is inevitable, thus avoiding inflammation of these intermediate areas.
  • a trapezoidal cross-section can be integrated into the burner much more simply, in particular two swirlers with respect to one another, so that an inflammation of these intermediate regions can be avoided even without intensive flushing with air.
  • Trapezoidal includes all geometries that has essentially two parallel sides. These can also have a slight curvature.
  • the corners of the boundary wall (B) can also have a rounding. All sides of the boundary wall (B) may have a slight bend.
  • the at least one swirl blade preferably has a 3-d geometry.
  • corner blades may be present in the corners of the boundary wall (B). These can be pointed and directed from the hub to the cross section or vice versa.
  • the corner vanes must also not consistently enough from the hub to the cross section. This ensures a better aerodynamic flow through the strongly 3-dimensional flow field.
  • the corners of the boundary wall (B) can be protected with effusion air. This avoids a flashback.
  • fuel can be passed through the hub.
  • fuel injections are arranged. These can be arranged on the swirl blades. During operation, fuel is thus injected into the air or the air / fuel mixture.
  • a swirler arrangement according to the invention is furthermore proposed, comprising at least two swirlers and a hub arranged along an axis (A, A ') and in each case with a boundary wall (B, B') which is at a distance from the hub and completely encloses the hub Swirl blade which extends radially outward from the hub to the boundary wall (B) and wherein the at least two Swirler are arranged like a ring.
  • the cross section of the at least two swirlers (90a, b) formed in each case by the boundary wall (B, B ') perpendicular to the axis (A, A') is non-circular in such a way that the smallest possible gap d1 is provided by the geometry of the cross sections between the boundary wall (B, B ') of the at least two Swirler is present.
  • the Swirler can also have a trapezoidal cross-section here. Due to the geometry of the Swirler the intermediate areas are significantly reduced and need less to be flushed with air. This air is now available for reducing the maximum temperatures and / or improving the mixture.
  • a burner with a swirler arrangement which comprises a pilot burner for supplying a fuel / fuel mixture and a pilot cone with a pilot combustion zone, wherein the swirlers are arranged annularly around the pilot burner, characterized in that the geometric shape of the swirlers is very close Placement of the Swirler on the pilot cone permits.
  • such a burner is used in a gas turbine.
  • FIG. 1 shows a burner 100 with a nozzle housing 6 and a lower part 5.
  • a pilot burner 1 which has an injection opening 4 for the pilot fuel, passes through the nozzle housing 6 and is fixed to the lower part 5 of the nozzle housing.
  • the main fuel nozzles 2 are parallel to the pilot burner 1 through the nozzle housing 6 and are fixed to the lower part 5 of the nozzle housing.
  • the fuel inlets 16 supply the main fuel nozzles 2 with fuel.
  • a main combustion zone 9 is formed within the liner 19.
  • a pilot cone 20 protrudes from the vicinity of the pilot fuel injection port 4 of the pilot burner 1 and has a widened end 22 adjacent to the main combustion zone 9.
  • the pilot cone 20 has an expanding profile forming a zone 23 for the pilot flame.
  • the compressed air 101 flows from the compressor 50 between support ribs 7 through the main air swirling devices 8 into the main combustion zone 9.
  • Each main air swirling device 8 is parallel to the pilot burner 1 and adjoins the main combustion zone 9.
  • a plurality of swirlers 80 surround each main fuel nozzle 2. These generate a swirl to mix compressed air 101 and fuel 102 together.
  • a fuel / air mixture 103 is carried to the main combustion zone where it burns.
  • the compressed air 101 also enters zone 23 of the pilot flame through a set of stationary sheets 10 located within pilot rotors 11.
  • the compressed air 101 mixes within the pilot cone 20 with the pilot fuel 30 and is in the zone 23 of the ignition or. Pilot flame transports where it burns.
  • FIG. 2 shows a view of a combustion chamber 100 along the axes AA.
  • the pilot burner 1 of main fuel nozzles 2 is annularly surrounded.
  • a main fuel swirling device 8 with swirlers 80 surrounds each main fuel nozzle 2.
  • the main fuel nozzles 8 are separated from each other by the distance d.
  • the pilot burner 1 is surrounded by main fuel nozzles 2, which are equidistantly spaced, but these distances may also vary.
  • the widened end 22 of the pilot cone 20 forms with the liner 19 a circular ring.
  • the fuel / air mixture flows through the annulus into the main combustion zone 19.
  • gaps In order to prevent an undesired ignition of the mixture between the main fuel nozzles 8, hereinafter referred to as gaps, these spaces of the main fuel nozzles 8 are thoroughly flushed with air. This air is limited for an improvement of the mixture and / or the reduction of the maximum combustion temperature available. Since it is known that leaner mixtures of fuel and air burn cooler and thus reduce the emission of NOx, it is desirable to minimize the required purge air in a simple manner.
  • FIG. 3 shows a Swirler 90 in particular for a gas turbine.
  • the swirler 90 has a boundary wall (B) which has a cross section formed perpendicular to the axis (A), this cross-section being trapezoidal.
  • the Swirler 90 comprises at least one swirl blade 91.
  • the swirler 90 is arranged substantially on a central hub 92. Through these takes place, the fuel supply.
  • the central hub 92 is connected to a fuel line.
  • the swirl blade 91 is preferably formed as a 3-D blade.
  • the fuel may be injected from the hub 92 or from the blades. This causes a better aerodynamic flow through the 3-dimensional flow field.
  • 3-d blades can be used.
  • corner blades 96 can be applied, which taper from the cross-sectional corners. These corner blades 96 are located in the corners of the boundary wall (B) and can reach to the hub 92; but also between the boundary wall (B) and hub 92 end. This achieves a better, more uniform flow behavior. Furthermore, it is advantageous that the corners of the boundary wall (B) are flowed through with effusion air, thus protecting these corners particularly well against flashback.
  • the swirl vanes 91 for fuel injection are fixedly connected to the boundary wall (B) of the Swirler 90. Alternatively, the swirl vanes 91 may also be connected only to the hub 92, are suspended as a component only on the hub 92, so to speak. This would be easier to produce in terms of production technology and thus cause lower costs.
  • FIG. 4 schematically shows a Swirleran Aunt 95 comprising the Swirler 90a, 90b. These are arranged centrally and annularly around a pilot burner 1.
  • the Swirler 90 a, 90b have a small distance d1 from each other. Due to the trapezoidal geometry of the cross sections, the swirlers can also be set very close to the plane of the pilot cone 20, since the advantageous geometric design precisely joins together the corresponding annular gap contour with segments in the circumferential direction.
  • a non-circular Swirler which has a circumferentially segmented flow creates, which is twisted each. Furthermore, it is possible with the aid of the invention to flow through the so-called interstices with substantially less air, so as to avoid unwanted inflammations of the interstices. Thus, more air is available for combustion. Another advantage is the simpler mechanical design and the associated greater robustness and lower production costs.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The swirler (90) is provided with a hub (92) arranged along an axle (A) and a limiting wall (B) for enclosing the hub. A swirl blade (91) is provided that extends from hub radially outward up to the limiting wall. The cross section formed by the limiting wall perpendicularly to the axle is trapezoidal. An independent claim is included for a blower with pilot combustion zone.

Description

Gasturbinen besitzen bekanntlich folgende Komponenten: einen Verdichter zum Verdichten von Luft; mindestens eine Brennkammer zum Erzeugen heißen Gases durch Verbrennen von Brennstoff in Anwesenheit der vom Kompressor gelieferten, verdichteten Luft; und eine Turbine, in der das von der Brennkammer gelieferte heiße Gas entspannt wird.Gas turbines are known to have the following components: a compressor for compressing air; at least one combustion chamber for generating hot gas by burning fuel in the presence of the compressed air supplied by the compressor; and a turbine in which the hot gas supplied from the combustion chamber is expanded.

Gasturbinen emittieren bekanntlich unerwünschte Stickoxide (NOx) und Kohlenmonoxid (CO). Ein bekannter Faktor, der die NOx-Emissionen beeinflusst, ist die Verbrennungstemperatur. Senkt man die Verbrennungstemperatur, so sinkt die Menge des abgegebenen NOx. Allerdings sind hohe Verbrennungstemperaturen wünschenswert, um einen hohen Wirkungsgrad zu erreichen und die CO-Oxidation zu verstärken. Es ist bekannt, dass magerere Brennstoff/Luft-Gemische kühler verbrennen und deshalb weniger NOx-Emissionen entstehen. Eine bekannte Technik zum Erzeugen eines magereren Brennstoffgemischs ist es, Turbulenzen zu erzeugen, um Luft und Brennstoff vor der Verbrennung so gleichmäßig wie möglich zu vermischen, um zu vermeiden, das Zonen mit fettem Gemisch entstehen, in denen es örtliche Stellen hoher Temperatur gibt (so genannt Hot Spots).Gas turbines are known to emit undesirable nitrogen oxides (NOx) and carbon monoxide (CO). One known factor affecting NOx emissions is the combustion temperature. If the combustion temperature is lowered, the amount of NOx released decreases. However, high combustion temperatures are desirable to achieve high efficiency and enhance CO oxidation. It is known that leaner fuel / air mixtures burn cooler and therefore less NOx emissions arise. One known technique for producing a leaner fuel mixture is to create turbulence to mix air and fuel as evenly as possible prior to combustion to avoid creating zones of rich mixture in which there are high temperature localities called hot spots).

Bei can, can annular Systemen insbesondere bei Vormischsystemen wird deshalb Brennstoff über einen Swirler (Drallerzeuger) zumeist mit Brennstoffeindüsung eingeströmt. Hierbei wird verdichtete Luft durch einen Kanal der Brennkammer zugeführt. In diesem Kanal wird der Swirler angeordnet, welcher mit mindestens einer Brennstoffleitung verbunden ist. Diese Swirler verdrallen die Verbrennungsluft und bringen gleichzeitig über Bohrungen Brennstoff in die Verbrennungsluft ein. Dieses Gemisch strömt dann der Brennkammer zu, um dort verbrannt zu werden. Durch dieses System wird eine möglichst homogene Durchmischung von Kraftstoff zu Luft erzielt, was wesentlich zur NOx Reduktion beiträgt.In the case of can, can annular systems, in particular in premix systems, therefore, fuel is mostly flowed in via a Swirler (swirl generator) with fuel injection. Here, compressed air is supplied through a channel of the combustion chamber. In this channel, the Swirler is arranged, which is connected to at least one fuel line. These swirlers twist the combustion air and at the same time introduce fuel into the combustion air through holes. This mixture then flows to the combustion chamber to be burned there. This system achieves the most homogeneous mixing possible from fuel to air, which contributes significantly to NOx reduction.

Bei Verbrennungsmaschinen, insbesondere solchen, die mit zwei verschiedenen Brennstoffen betrieben werden, erfolgt beispielsweise eine Eindüsung des Brennstoffes Öl über Swirler, in denen das Öl mit Luft vermischt wird. Diese Swirler sind um einen stark verdrallten Pilotbrenner zumeist konzentrisch angeordnet. Dem Piloten ist ein Pilotkonus nachgeordnet, in welchem die Pilotgasverbrennung stattfindet. Diesem, in Strömungsrichtung nachgeschaltet, findet die Hauptverbrennung statt. Brennluft strömt durch den Piloten bzw. den Swirler und wird dort mit Brennstoff gemischt. Um eine unerwünschte Entzündung des Gemisches zu verhindern, werden die Zwischengebiete zwischen den Swirlern mit Luft bzw. einem Luft/Brennstoffgemisch durchströmt. Diese Luft steht für eine Verbesserung der Mischung und /oder für eine Reduktion der maximalen Verbrennungstemperatur nur begrenzt zur Verfügung.In combustion engines, in particular those which are operated with two different fuels, for example, an injection of the fuel oil via Swirler, in which the oil is mixed with air. These swirlers are usually arranged concentrically around a heavily twisted pilot burner. The pilot is followed by a pilot cone, in which the pilot gas combustion takes place. This, downstream in the flow direction, the main combustion takes place. Combustion air flows through the pilot or the Swirler and is mixed there with fuel. To prevent unwanted ignition of the mixture, the intermediate areas between the swirlers are traversed by air or an air / fuel mixture. This air is available for an improvement of the mixture and / or for a reduction of the maximum combustion temperature only limited.

Die U 6,038,861 offenbart einen Swirler, welche an der Brennlufteingangsseite einen runden Querschnitt aufweisen. Diese erweitern sich mit zunehmender Strömungsrichtung. Angrenzende Swirler schließen sich schließlich zu einem Ringspalt zusammenschließen. Fertigungsseitig ist dies jedoch nur schwer umzusetzen.The U 6,038,861 discloses a Swirler, which have a round cross-section at the combustion air inlet side. These expand with increasing flow direction. Adjacent swirlers eventually join together to form an annular gap. However, this is difficult to implement on the production side.

Es ist daher eine erste Aufgabe der vorliegenden Erfindung, einen Swirler zur Verfügung zu stellen, welcher die oben genannten Nachteile beseitigt. Eine zweite Aufgabe der vorliegenden Erfindung besteht in der Offenbarung einer vorteilhaften Swirleranordnung. Eine weitere Aufgabe der Erfindung ist es, einen vorteilhaften Brenner zur Verfügung zu stellen.It is therefore a first object of the present invention to provide a swirler which overcomes the above disadvantages. A second object of the present invention is to disclose an advantageous swirler arrangement. Another object of the invention is to provide an advantageous burner.

Die Aufgabe wird gelöst durch die Angabe einer Swirler nach Anspruch 1. Die weitere Aufgabe wird gelöst durch die Angabe einer Swirleranordnung nach Anspruch 8. Die auf den Brenner bezogene Aufgabe wird gelöst durch die Angabe eines Brenners nach Anspruch 10.The object is achieved by the specification of a swirler according to claim 1. The further object is achieved by the specification of a swirler arrangement according to claim 8. The object related to the burner is achieved by the specification of a burner according to claim 10.

Erstmals wird somit vorgeschlagen einen Swirler mit einer entlang einer Achse (A) angeordneten Nabe und mit einer die Nabe vollumfänglich umschließenden von der Nabe beanstandeten Begrenzungswand (B) auszubilden, wobei dieser Swirler mindestens eine Drallschaufel umfasst, welche sich von der Nabe radial auswärts gerichtet bis zur Begrenzungswand (B) erstreckt. Erfindungsgemäß ist dabei der durch die Begrenzungswand (B) senkrecht zur Achse (A) gebildete Querschnitt trapezoidförmig. Die Erfindung hat somit erkannt, dass bei der derzeitigen Geometrie der Swirler eine intensive Durchströmung der Zwischengebiete mit Luft unumgänglich ist, um somit eine Entzündung dieser Zwischengebiete zu vermeiden. Ein trapezoidförmiger Querschnitt hingegen lässt sich wesentlich vereinfacht in den Brenner integrieren, insbesondere zwei Swirler zueinander, so dass eine Entzündung dieser Zwischengebiete auch ohne intensives Spülen mit Luft vermieden werden kann. Dabei umfasst trapezoid alle Geometrien, die im Wesentlichen zwei parallele Seiten aufweist. Diese können auch eine leichte Krümmung aufweisen. Die Ecken der Begrenzungswand (B) können dabei auch eine Rundung aufweisen. Alle Seiten der Begrenzungswand (B)können eine leichte Biegung aufweisen.For the first time, it is thus proposed to form a swirler with a hub arranged along an axis (A) and with a boundary wall (B) completely surrounding the hub, said swirler comprising at least one swirl blade directed radially outwards from the hub extends to the boundary wall (B). According to the invention, the cross section formed by the boundary wall (B) perpendicular to the axis (A) is trapezoidal. The invention has thus recognized that in the current geometry of the Swirler an intensive flow through the intermediate areas with air is inevitable, thus avoiding inflammation of these intermediate areas. By contrast, a trapezoidal cross-section can be integrated into the burner much more simply, in particular two swirlers with respect to one another, so that an inflammation of these intermediate regions can be avoided even without intensive flushing with air. Trapezoidal includes all geometries that has essentially two parallel sides. These can also have a slight curvature. The corners of the boundary wall (B) can also have a rounding. All sides of the boundary wall (B) may have a slight bend.

Bevorzugt weist die mindestens eine Drallschaufel eine 3-d Geometrie auf. Zusätzlich können in den Ecken der Begrenzungswand (B) Eckschaufeln vorhanden sein. Diese können spitz zulaufen und von der Nabe zum Querschnitt gerichtet sein oder umgekehrt. Die Eckschaufeln müssen ebenfalls nicht durchgängig von der Nabe zum Querschnitt reichen. Dies sorgt für eine bessere aerodynamische Durchströmung des stark 3-dimensionalen Strömungsfeldes.The at least one swirl blade preferably has a 3-d geometry. In addition, corner blades may be present in the corners of the boundary wall (B). These can be pointed and directed from the hub to the cross section or vice versa. The corner vanes must also not consistently enough from the hub to the cross section. This ensures a better aerodynamic flow through the strongly 3-dimensional flow field.

Zusätzlich können die Ecken der Begrenzungswand (B) mit Effusionsluft geschützt werden. Dies vermeidet einen Flammenrückschlag.In addition, the corners of the boundary wall (B) can be protected with effusion air. This avoids a flashback.

Bevorzugt ist durch die Nabe Brennstoff führbar.Preferably, fuel can be passed through the hub.

In bevorzugter Ausgestaltung sind Brennstoffeindüsungen angeordnet. Diese können an den Drallschaufeln angeordnet sein. Bei Betrieb wird so Brennstoff in die Luft bzw. das Luft / Brennstoffgemisch eingedüst.In a preferred embodiment, fuel injections are arranged. These can be arranged on the swirl blades. During operation, fuel is thus injected into the air or the air / fuel mixture.

Es wird weiterhin erfindungemäß eine Swirleranordnung vorgeschlagen, mit mindestens zwei Swirlern und mit einer jeweils entlang einer Achse (A, A') angeordneten Nabe sowie jeweils mit einer die Nabe vollumfänglich umschließenden von der Nabe beabstandeten Begrenzungswand (B, B') umfassend jeweils mindestens einer Drallschaufel welche sich von Nabe radial auswärts gerichtet bis zur Begrenzungswand (B) erstreckt und wobei die mindestens zwei Swirler ringartig angeordnet sind. Erfindungsgemäß ist der jeweils durch die Begrenzungswand (B,B') senkrecht zur Achse (A,A') gebildete Querschnitt der mindestens zwei Swirler (90a,b) nichtrund ausgebildet und zwar dergestalt, dass durch die Geometrie der Querschnitte ein möglichst kleiner Spalt d1 zwischen der Begrenzungswand (B,B') der mindestens zwei Swirler vorhanden ist. Die Swirler können auch hier einen trapezoidförmigen Querschnitt aufweisen. Durch die Geometrie der Swirler werden die Zwischengebiete wesentlich verkleinert und brauchen weniger mit Luft durchspült werden. Diese Luft steht nun der Reduktion der maximalen Temperaturen und /oder einer Verbesserung der Mischung zur Verfügung.A swirler arrangement according to the invention is furthermore proposed, comprising at least two swirlers and a hub arranged along an axis (A, A ') and in each case with a boundary wall (B, B') which is at a distance from the hub and completely encloses the hub Swirl blade which extends radially outward from the hub to the boundary wall (B) and wherein the at least two Swirler are arranged like a ring. According to the invention, the cross section of the at least two swirlers (90a, b) formed in each case by the boundary wall (B, B ') perpendicular to the axis (A, A') is non-circular in such a way that the smallest possible gap d1 is provided by the geometry of the cross sections between the boundary wall (B, B ') of the at least two Swirler is present. The Swirler can also have a trapezoidal cross-section here. Due to the geometry of the Swirler the intermediate areas are significantly reduced and need less to be flushed with air. This air is now available for reducing the maximum temperatures and / or improving the mixture.

Erfindungsgemäß wird weiterhin ein Brenner mit einer Swirleranordnung offenbart, welcher einen Pilotbrenner zur Zuführung von einem Brennstoff / Brennstoffgemisch sowie einem Pilotkegel mit einer Pilotverbrennungszone umfaßt, wobei die Swirler ringförmig um den Pilotbrenner angeordnet sind, dadurch gekennzeichnet, dass die geometrische Form der Swirler eine sehr nahe Platzierung der Swirler am Pilotkegel zulässt.According to the invention, a burner with a swirler arrangement is disclosed, which comprises a pilot burner for supplying a fuel / fuel mixture and a pilot cone with a pilot combustion zone, wherein the swirlers are arranged annularly around the pilot burner, characterized in that the geometric shape of the swirlers is very close Placement of the Swirler on the pilot cone permits.

Bevorzugt wird ein solcher Brenner in einer Gasturbine verwendet.Preferably, such a burner is used in a gas turbine.

Die Erfindung wird beispielhaft und teilweise schematisch anhand der Zeichnung erläutert. Es zeigen:

FIG 1
zeigt schematisch einen Schnitt durch einen Brenner nach dem Stand der Technik,
FIG 2
zeigt schematisch einen radialen Querschnitt eines Brenners entlang der Schnittlinie A-A von Fig. 1,
FIG 3
zeigt einen erfindungsgemäßen Swirler,
FIG 4
zeigt eine erfindungsgemäße Swirleranordnung mit Piloten.
The invention will be explained by way of example and in part schematically with reference to the drawing. Show it:
FIG. 1
shows schematically a section through a burner according to the prior art,
FIG. 2
schematically shows a radial cross-section of a burner along the section line AA of Fig. 1 .
FIG. 3
shows a Swirler invention,
FIG. 4
shows a Swirleranordnung with pilots invention.

Gleiche Bezugszeichen haben in den verschiedenen Figuren die gleiche Bedeutung.Like reference numerals have the same meaning in the various figures.

FIG 1 zeigt einen Brenner 100 mit einem Düsengehäuse 6 und einem Unterteil 5. Ein Pilotbrenner 1, der eine Einspritzöffnung 4 für den Zündbrennstoff auf weist, verläuft durch das Düsengehäuse 6 und ist an dem Unterteil 5 des Düsengehäuses befestigt. Die Hauptbrennstoffdüsen 2 verlaufen parallel zu dem Pilotbrenner 1 durch das Düsengehäuse 6 und sind an dem Unterteil 5 des Düsengehäuses befestigt. Die Brennstoffeinlässe 16 versorgen die Hauptbrennstoffdüsen 2 mit Brennstoff. FIG. 1 shows a burner 100 with a nozzle housing 6 and a lower part 5. A pilot burner 1, which has an injection opening 4 for the pilot fuel, passes through the nozzle housing 6 and is fixed to the lower part 5 of the nozzle housing. The main fuel nozzles 2 are parallel to the pilot burner 1 through the nozzle housing 6 and are fixed to the lower part 5 of the nozzle housing. The fuel inlets 16 supply the main fuel nozzles 2 with fuel.

Eine Hauptverbrennungszone 9 wird innerhalb der Auskleidung 19 gebildet. Ein Pilotkegel 20 ragt aus der Nähe der Einspritzöffnung 4 für den Zündbrennstoff des Pilotbrenners 1 hervor und hat neben der Hauptverbrennungszone 9 ein verbreitertes Ende 22. Der Pilotkegel 20 hat ein sich erweiterndes Profil, das eine Zone 23 für die Zündflamme bildet.A main combustion zone 9 is formed within the liner 19. A pilot cone 20 protrudes from the vicinity of the pilot fuel injection port 4 of the pilot burner 1 and has a widened end 22 adjacent to the main combustion zone 9. The pilot cone 20 has an expanding profile forming a zone 23 for the pilot flame.

Die verdichtete Luft 101 strömt von dem Verdichter 50 zwischen Stützrippen 7 durch die Hauptluftverwirbelungsvorrichtungen 8 in die Hauptverbrennungszone 9. Jede Hauptluftverwirbelungsvorrichtung 8 ist parallel zu dem Pilotbrenner 1 und grenzt an die Hauptverbrennungszone 9 an. Eine Vielzahl von Swirlern 80 umgibt jede Hauptbrennstoffdüse 2. Diese generieren eine Verwirbelung um verdichtete Luft 101 und Brennstoff 102 miteinander zu mischen. Ein Brennstoff/Luft Gemisch 103 wird in die Hauptverbrennungszone getragen, wo es verbrennt.The compressed air 101 flows from the compressor 50 between support ribs 7 through the main air swirling devices 8 into the main combustion zone 9. Each main air swirling device 8 is parallel to the pilot burner 1 and adjoins the main combustion zone 9. A plurality of swirlers 80 surround each main fuel nozzle 2. These generate a swirl to mix compressed air 101 and fuel 102 together. A fuel / air mixture 103 is carried to the main combustion zone where it burns.

Die verdichtete Luft 101 dringt ebenfalls durch einen Satz von stationäre Blechen 10, die sich innerhalb der Pilotswirler 11 befinden, in die Zone 23 der Zündflamme ein. Die verdichtete Luft 101 vermischt sich innerhalb des Pilotkegels 20 mit dem Zündbrennstoff 30 und wird in die Zone 23 der Zünd-bzw. Pilotflamme transportiert, wo sie verbrennt.The compressed air 101 also enters zone 23 of the pilot flame through a set of stationary sheets 10 located within pilot rotors 11. The compressed air 101 mixes within the pilot cone 20 with the pilot fuel 30 and is in the zone 23 of the ignition or. Pilot flame transports where it burns.

FIG 2 zeigt eine Ansicht einer Brennkammer 100 entlang der Achsen A-A. Wie in Fig. 2 gezeigt, ist der Pilotbrenner 1 von Hauptbrennstoffdüsen 2 ringartig umgeben. Eine Hauptbrennstoffverwirbelungsvorrichtungen 8 mit Swirlern 80 umgibt jede Hauptbrennstoffdüse 2. Die Hauptbrennstoffdüsen 8 sind voneinander durch den Abstand d getrennt. In dieser Ausführung wird der Pilotbrenner 1 von Hauptbrennstoffdüsen 2, welche in gleichem Abstand voneinander angeordnet sind, umgeben, jedoch können diese Abstände auch variieren. Das verbreiterte Ende 22 des Pilotkegels 20 bildet mit der Auskleidung 19 einen Kreisring. Das Brennstoff/Luft Gemisch fließt durch den Kreisring in die Hauptverbrennungszone 19. FIG. 2 shows a view of a combustion chamber 100 along the axes AA. As in Fig. 2 shown, the pilot burner 1 of main fuel nozzles 2 is annularly surrounded. A main fuel swirling device 8 with swirlers 80 surrounds each main fuel nozzle 2. The main fuel nozzles 8 are separated from each other by the distance d. In this embodiment, the pilot burner 1 is surrounded by main fuel nozzles 2, which are equidistantly spaced, but these distances may also vary. The widened end 22 of the pilot cone 20 forms with the liner 19 a circular ring. The fuel / air mixture flows through the annulus into the main combustion zone 19.

Um nun eine unerwünschte Entzündung des Gemisches zwischen den Hauptbrennstoffdüsen 8, nachfolgend als Zwischenräume bezeichnet, zu verhindern, werden diese Zwischenräume der Hauptbrennstoffdüsen 8 intensiv mit Luft durchspült. Diese Luft steht für eine Verbesserung der Mischung und /oder der Reduktion der maximalen Verbrennungstemperatur nur begrenzt zur Verfügung. Da bekannt ist, dass magerere Gemische aus Brennstoff und Luft kühler verbrennen und damit die Emission von NOx senken, ist es wünschenswert, die benötigte Spülluft auf einfache Art und Weise zu minimieren.In order to prevent an undesired ignition of the mixture between the main fuel nozzles 8, hereinafter referred to as gaps, these spaces of the main fuel nozzles 8 are thoroughly flushed with air. This air is limited for an improvement of the mixture and / or the reduction of the maximum combustion temperature available. Since it is known that leaner mixtures of fuel and air burn cooler and thus reduce the emission of NOx, it is desirable to minimize the required purge air in a simple manner.

FIG 3 zeigt einen Swirler 90 insbesondere für eine Gasturbine. Der Swirler 90 weist eine Begrenzungswand (B) auf, welche einen senkrecht zur Achse (A) gebildeten Querschnitt aufweist, wobei dieser Querschnitt trapezoidförmig ist. Der Swirler 90 umfaßt dabei mindestens eine Drallschaufel 91. Der Swirler 90 ist im Wesentlichen auf einer zentralen Nabe 92 angeordnet. Durch diese erfolgt auch die Brennstoffversorgung. Dazu ist die zentrale Nabe 92 mit einer Brennstoffleitung verbunden. Die Drallschaufel 91 ist dabei bevorzugt als 3-d Schaufel ausgebildet. Der Brennstoff kann aus der Nabe 92 oder aus den Schaufeln eingedüst werden. Die bewirkt eine bessere aerodynamische Durchströmung des 3-dimensionalen Strömungsfeld. Insbesondere in den Ecken der Begrenzungswand (B) können 3-d Schaufeln verwendet werden. Zusätzlich können in den Ecken der Begrenzungswand (B) auch Eckschaufeln 96 angelegt werden, welche von den Querschnittsecken spitz zulaufen. Diese Eckschaufeln 96 sind in den Ecken der Begrenzungswand (B) angeordnet und können bis zur Nabe 92 reichen; jedoch auch zwischen Begrenzungswand (B) und Nabe 92 enden. Dadurch wird ein besseres, gleichmäßigeres Strömungsverhalten erzielt. Weiterhin ist es vorteilhaft, dass die Ecken der Begrenzungswand (B) mit Effusionsluft durchströmt werden, um somit diese Ecken besonders gut gegen Flammenrückschlag zu schützen. Die Drallschaufeln 91 zur Brennstoffeindüsung sind mit der Begrenzungswand (B) der Swirler 90 fest verbunden. Alternativ können die Drallschaufeln 91 auch lediglich mit der Nabe 92 verbunden sein, sind sozusagen als Bauteil nur an der Nabe 92 aufgehängt. Dies würde fertigungstechnisch einfacher herstellbar sein und somit geringere Kosten verursachen. FIG. 3 shows a Swirler 90 in particular for a gas turbine. The swirler 90 has a boundary wall (B) which has a cross section formed perpendicular to the axis (A), this cross-section being trapezoidal. Of the Swirler 90 comprises at least one swirl blade 91. The swirler 90 is arranged substantially on a central hub 92. Through these takes place, the fuel supply. For this purpose, the central hub 92 is connected to a fuel line. The swirl blade 91 is preferably formed as a 3-D blade. The fuel may be injected from the hub 92 or from the blades. This causes a better aerodynamic flow through the 3-dimensional flow field. In particular in the corners of the boundary wall (B) 3-d blades can be used. In addition, in the corners of the boundary wall (B) also corner blades 96 can be applied, which taper from the cross-sectional corners. These corner blades 96 are located in the corners of the boundary wall (B) and can reach to the hub 92; but also between the boundary wall (B) and hub 92 end. This achieves a better, more uniform flow behavior. Furthermore, it is advantageous that the corners of the boundary wall (B) are flowed through with effusion air, thus protecting these corners particularly well against flashback. The swirl vanes 91 for fuel injection are fixedly connected to the boundary wall (B) of the Swirler 90. Alternatively, the swirl vanes 91 may also be connected only to the hub 92, are suspended as a component only on the hub 92, so to speak. This would be easier to produce in terms of production technology and thus cause lower costs.

FIG 4 zeigt schematisch eine Swirleranordnung 95 umfassend die Swirler 90a,90b. Diese sind zentral und ringförmig um einen Pilotbrenner 1 angeordnet. Die Swirler 90 a, 90b weisen einen geringen Abstand d1 voneinander auf. Durch die trapezoide Geometrie der Querschnitte können die Swirler auch sehr nahe an die Ebene des Pilotkegels 20 gesetzt werden, da durch die vorteilhafte geometrische Ausführung eben die entsprechende Ringspaltkontur mit Segmenten in Umfangsrichtung zusammengesellt wird. FIG. 4 schematically shows a Swirleranordnung 95 comprising the Swirler 90a, 90b. These are arranged centrally and annularly around a pilot burner 1. The Swirler 90 a, 90b have a small distance d1 from each other. Due to the trapezoidal geometry of the cross sections, the swirlers can also be set very close to the plane of the pilot cone 20, since the advantageous geometric design precisely joins together the corresponding annular gap contour with segments in the circumferential direction.

Durch diese Erfindung wird ein unrunder Swirler geschaffen, welcher eine in Umfangsrichtung segmentierte Strömung schafft, die jeweils verdrallt ist. Weiterhin ist es mit Hilfe der Erfindung möglich, die so genannten Zwischenräume mit wesentlich weniger Luft zu durchströmen, um somit unerwünschte Entzündungen der Zwischenräume zu vermeiden. Somit steht mehr Luft der Verbrennung zur Verfügung. Ein weiterer Vorteil ist die einfachere mechanische Ausführung und die damit verbundene größere Robustheit und geringere Herstellungskosten.By this invention, a non-circular Swirler is provided, which has a circumferentially segmented flow creates, which is twisted each. Furthermore, it is possible with the aid of the invention to flow through the so-called interstices with substantially less air, so as to avoid unwanted inflammations of the interstices. Thus, more air is available for combustion. Another advantage is the simpler mechanical design and the associated greater robustness and lower production costs.

Claims (12)

Swirler (90) mit einer entlang einer Achse (A) angeordneten Nabe (92) und mit einer die Nabe (92) vollumfänglich umschließenden von der Nabe beanstandeten Begrenzungswand (B) umfassend mindestens einer Drallschaufel (91), welche sich von Nabe (92) radial auswärts gerichtet bis zur Begrenzungswand (B) erstreckt, dadurch gekennzeichnet, dass der durch die Begrenzungswand (B) senkrecht zur Achse (A) gebildete Querschnitt trapezoidförmig ist.A swirler (90) having a hub (92) disposed along an axis (A) and having a boundary wall (B) fully enclosed by the hub (92) and comprising at least one swirl vane (91) extending from the hub (92). extends radially outwardly to the boundary wall (B), characterized in that the cross section formed by the boundary wall (B) perpendicular to the axis (A) is trapezoidal. Swirler (90) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die mindestens eine Drallschaufel (91) eine 3-d Geometrie aufweist.Swirler (90) according to one of the preceding claims,
characterized in that the at least one swirl blade (91) has a 3-d geometry. Swirler (90) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass in den Ecken der Begrenzungswand (B) Eckschaufeln (96) vorhanden sind.Swirler (90) according to one of the preceding claims,
characterized in that in the corners of the boundary wall (B) corner blades (96) are present. Swirler (90) nach Anspruch 3, dadurch gekennzeichnet, dass die Eckschaufeln (96) spitz zulaufen.Swirler (90) according to claim 3, characterized in that the corner blades (96) are tapered. Swirler (90) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass durch die Nabe (92) Brennstoff führbar ist.Swirler (90) according to one of the preceding claims,
characterized in that through the hub (92) fuel is feasible. Swirler (90) nach Anspruch 5,
dadurch gekennzeichnet, dass Brennstoffeindüsungen umfasst sind.Swirler (90) according to claim 5,
characterized in that fuel injections are included. Swirler (90) nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass durch die Nabe (92) Brennstoff in die Drallschaufeln (91) leitbar ist und dort ausgedüst wird und/oder Brennstoff zusätzlich ausgehend von der Nabe ausgedüst wird.Swirler (90) according to one of the preceding claims,
characterized in that through the hub (92) fuel in the swirl vanes (91) can be conducted and is emptied there and / or fuel is additionally emptied starting from the hub. Swirler (90) nach einem der vorhergehenden Ansprüche dadurch gekennzeichnet, dass die Begrenzungswand und/oder Ecken der Begrenzungswand (B) mit Effusionsluft geschützt werden.Swirler (90) according to one of the preceding claims, characterized in that the boundary wall and / or Corners of the boundary wall (B) to be protected with effusion air. Swirleranordnung (95) mit mindestens zwei Swirlern (90a,90b) mit einer jeweils entlang einer Achse (A, A') angeordneten Nabe (92) sowie jeweils mit einer die Nabe (92) vollumfänglich umschließenden von der Nabe (92) beanstandeten Begrenzungswand (B, B') umfassend mindestens einer Drallschaufel (91), welche sich von Nabe (92) radial auswärts gerichtet bis zur Begrenzungswand (B) erstreckt, wobei die mindestens zwei Swirler (90a,b) ringartig angeordnet sind,
dadurch gekennzeichnet, dass der jeweils durch die Begrenzungswand (B,B') senkrecht zur Achse (A,A') gebildete Querschnitt der mindestens zwei Swirler (90a,b) nichtrund ausgebildet ist und zwar dergestalt, dass durch die Geometrie der Querschnitte ein möglichst kleiner Spalt d1 zwischen der Begrenzungswand (B,B') der mindestens zwei Swirler (90a,90b) vorhanden ist.Swirling arrangement (95) with at least two swirlers (90a, 90b) with a hub (92) arranged along one axis (A, A ') and each with a boundary wall (92) completely surrounded by the hub (92) ( B, B ') comprising at least one swirl blade (91) which extends radially outward from the hub (92) to the boundary wall (B), wherein the at least two swirlers (90a, b) are arranged in an annular manner,
characterized in that each of the boundary wall (B, B ') perpendicular to the axis (A, A') formed cross section of the at least two Swirler (90a, b) is non-circular in such a way that by the geometry of the cross sections as possible small gap d1 between the boundary wall (B, B ') of the at least two Swirler (90a, 90b) is present. Swirleranordnung (95) nach Anspruch 9,
dadurch gekennzeichnet, dass der mindestens eine Swirler (90a)(90b) ein Swirler (90) nach einem der Ansprüche 1-8 ist.Swirl arrangement (95) according to claim 9,
characterized in that the at least one swirler (90a) (90b) is a swirler (90) according to any one of claims 1-8. Brenner (100) mit einer Swirleranordnung nach einen der Ansprüche 9 oder 10,
dadurch gekennzeichnet, dass ein Pilotbrenner (1) zur Zuführung von einem Brennstoff/Brennstoffgemisches sowie einem Pilotkegel (20) mit einer Pilotverbrennungszone (23) umfasst wird, wobei die Swirler (90a,b) ringförmig um den Pilotbrenner (1) angeordnet ist, dadurch gekennzeichnet, dass die geometrische Form der Swirler (90) eine sehr nahe Platzierung der Swirler (90) am Pilotkegel (20) zulässt.Burner (100) with a swirling arrangement according to one of claims 9 or 10,
characterized in that a pilot burner (1) for supplying a fuel / fuel mixture and a pilot cone (20) having a pilot combustion zone (23), said swirler (90a, b) annularly around the pilot burner (1) is arranged, characterized characterized in that the geometric shape of the Swirler (90) allows a very close placement of the Swirler (90) on the pilot cone (20). Gasturbine mit einem Brenner nach Anspruch 11.Gas turbine with a burner according to claim 11.
EP08013950A 2008-08-04 2008-08-04 Swirler Not-in-force EP2151630B1 (en)

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EP08013950A EP2151630B1 (en) 2008-08-04 2008-08-04 Swirler
AT08013950T ATE528589T1 (en) 2008-08-04 2008-08-04 SWIRLERS
JP2009179079A JP5574635B2 (en) 2008-08-04 2009-07-31 Swirl

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JP2010038538A (en) 2010-02-18
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JP5574635B2 (en) 2014-08-20

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