EP0122526A1 - Fuel injector for the combustion chamber of a gas turbine - Google Patents

Fuel injector for the combustion chamber of a gas turbine Download PDF

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Publication number
EP0122526A1
EP0122526A1 EP84103522A EP84103522A EP0122526A1 EP 0122526 A1 EP0122526 A1 EP 0122526A1 EP 84103522 A EP84103522 A EP 84103522A EP 84103522 A EP84103522 A EP 84103522A EP 0122526 A1 EP0122526 A1 EP 0122526A1
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EP
European Patent Office
Prior art keywords
fuel
combustion chamber
lance
nozzle outlet
passage openings
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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
EP84103522A
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German (de)
French (fr)
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EP0122526B1 (en
Inventor
Laan Dr. Hellat
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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Publication of EP0122526A1 publication Critical patent/EP0122526A1/en
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Publication of EP0122526B1 publication Critical patent/EP0122526B1/en
Expired legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a fuel lance according to the preamble of patent claim 1.
  • Self-excited vibrations can occur in combustion chambers, which are based on a modulation of the gaseous fuel or fuel-air mixture quantity injected into the combustion chamber by pressure fluctuations in the nozzle plane.
  • the feedback loop necessary for self-excitation is closed when the changes in the fuel conversion in the flame caused by the supply fluctuations meet a phase condition with the chamber pressure.
  • a classic example of this is the so-called "singing flame”.
  • the object of the invention is to provide a burner which combines the above-described decoupling of the burner fuel line to avoid combustion chamber vibrations with the possibility of regulating the amount of fuel.
  • the advantage of the invention can essentially be seen in the fact that a fuel lance is created in a relatively simple manner, which combines both a decoupling of the fuel line to avoid combustion chamber vibrations and the possibility of regulating the amount of fuel in a compact manner.
  • the decoupling is effective insofar as the distance between the throttle body and Nozzle outlet can be kept much shorter than the wavelength of typical natural vibrations of the combustion chamber system.
  • the fuel lance can optionally be designed with a central or radial nozzle outlet.
  • the throttle body also acts as a flame arrester.
  • a fuel lance 1 which is part of a burner, not shown, which in turn is part of a combustion chamber, also not shown, for example a gas turbine.
  • the burner can be, for example, a diffusion burner with a swirled air supply.
  • the fuel lance 1 consists of a lance tube 2 with a central nozzle outlet 3. Upstream of the lance tube 2, the fuel lance 1 is formed by a bush 4 in which an axially adjustable tubular throttle body 5 is guided. The fuel 7 is supplied through the pipe interior 6. Downstream, the tube wall 8 in the unguided part of the throttle body 5 is provided with fuel passage openings 9 in the circumferential direction and in the axial direction. Both their number and arrangement are arbitrary; As far as the shape is concerned, holes or slots can be provided, for example. As far as the number and size of the fuel passage openings 9 are concerned, they depend on the maximum required throughput of the respective burner.
  • the lance tube 2 carries a stamp 10 in the interior of the tube, which is mounted centrally to the tube interior 6 of the throttle body 5 by means of webs 11 - as are usually used to support inner bodies when cross-sections flow through.
  • a seal 12 also placed there ensures that the fuel passage openings 9 located above the plunger 10 in the respective axial position of the throttle body 5 are closed gas-tight.
  • the gas tightness between the throttle body 5 and the sleeve 4 is brought about by a seal 13.
  • the released flow cross section thus depends on the respective penetration depth of the plunger 10 relative to the throttle body 5. If the ratio of the fuel pressure in the supply line to the pressure at the nozzle outlet 3 exceeds a critical value, the fuel 7 flows through the fuel passage openings 9 in the throttle body 5 at the speed of sound, so that pressure disturbances running upstream from the nozzle outlet 3 cause the pressure from the combustion Material passage openings 9 can no longer influence emerging fuel quantity 7a. In terms of design, it is important to note that the distance between fuel passage openings 9 and nozzle outlet 3 or 15 is considerably shorter than the wavelength of typical natural vibrations of the combustion chamber system.
  • FIG. 2 similar to FIG. 1, a greatly simplified illustration of a fuel lance 1 is also shown.
  • This embodiment is distinguished from FIG. 1 by the difference that the fuel quantity 7a flowing through now emerges radially from the fuel lance 1.
  • the lance tube 2 is continuously cylindrical and is open on the nozzle outlet side.
  • the punch 10 is extended over the webs 11 and carries a central body 14 at its end. The opening between the end of the lance tube 2 and the inside runout curve of the central body 14 forms the radial nozzle outlet 15.
  • the fuel 7 is fed directly through the fuel lance 1. Downstream the lance tube 2 runs into a bushing 16 which extends up to the central nozzle outlet 3.
  • the throttle body 5 is a spindle which is only tubularly recessed at the end and only over a certain length.
  • the fuel passage openings 9 are also provided in this section.
  • the inner diameter of the sleeve 16 also forms the opening to the central nozzle outlet 3.
  • the fuel flows through that combustion Substance passage openings 9, which are still in use due to the fuel quantity regulation, ie are not yet covered by the sleeve 16.
  • the fuel 7 flows from the outside into the interior of the throttle body 5 in order to reach the nozzle outlet 3 from here.
  • Fig. 4 shows a lance tube 2 open on both sides, which is divided in the middle by a constriction 17.
  • the constriction fulfills the same function as the bush 16, described under FIG. 3.
  • the central body 14 enables a radial nozzle outlet 15.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)

Abstract

Bei Brennkammern von Gasturbinen können selbsterregte Schwingungen auftreten, die auf einer Modulation der in die Brennkammer eingedüsten gasförmigen Brennstoff- oder Brennstoff-Luftgemisch-Menge durch Druckschwankungen in der Düsenebene beruhen. Die neue Brennstofflanze (1) ermöglicht gleichzeitig sowohl eine Abkopplung der Brennstoff-leitung zur Vermeidung von Brennkammerschwingungen als auch die Möglichkeit der Brennstoffmengenregulierung. Die Brennstofflanze (1) trägt einen verstellbaren, mit Brennstoffdurchtrittöffnungen (9) versehenen Dorsselkörper (5), dessen Eindringtiefe gegenüber dem festen Körper (10) ein Mass für die durchströmende Brennstoffmenge (7a) ist.Self-excited vibrations can occur in combustion chambers of gas turbines, which are based on modulation of the gaseous fuel or fuel-air mixture quantity injected into the combustion chamber by pressure fluctuations in the nozzle plane. The new fuel lance (1) enables both the fuel line to be disconnected to avoid combustion chamber vibrations and the possibility of regulating the amount of fuel. The fuel lance (1) carries an adjustable, with fuel passage openings (9) provided Dorsselkörper (5), the depth of penetration compared to the solid body (10) is a measure of the amount of fuel flowing through (7a).

Description

Die Erfindung betrifft eine Brennstofflanze gemäss dem Oberbegriff des Patentanspruchs 1.The invention relates to a fuel lance according to the preamble of patent claim 1.

In Brennkammern können selbsterregte Schwingungen auftreten, die auf einer Modulation der in die Brennkammer eingedüsten gasförmigen Brennstoff- oder Brennstoff-Luftgemisch-Menge durch Druckschwankungen in der Düsenebene beruhen. Der für die Selbsterregung notwendige Rückkopplungskreis ist dann geschlossen, wenn die von der Zufuhrschwankungen bewirkten Aenderungen des Brennstoffumsatzes in der Flamme mit dem Kammerdruck eine Phasenbedingung erfüllen. Ein klassisches Beispiel hierfür ist die sogenannte "singende Flamme".Self-excited vibrations can occur in combustion chambers, which are based on a modulation of the gaseous fuel or fuel-air mixture quantity injected into the combustion chamber by pressure fluctuations in the nozzle plane. The feedback loop necessary for self-excitation is closed when the changes in the fuel conversion in the flame caused by the supply fluctuations meet a phase condition with the chamber pressure. A classic example of this is the so-called "singing flame".

Solche Schwingungen lassen sich im wesentlichen auf zwei Arten bekämpfen:

  • 1. Durch Aenderung der akustischen Eigenschaften, d.h. der Impedanzen der Brennstoffzuleitung oder der Kammer. Diese Massnahmen wirken allerdings nur in einem bestimmten Frequenzband, da die Impedanzen von der Frequenz abhängen.
  • 2. Durch akustische Abkopplung des Brennstoffzufuhrsystems mit einer unendlich grossen Eintrittsimpedanz. Man erreicht dies über eine starke Drosselung der Brennstoffzufuhr in der Nähe des Brennkammereintritts, z.B. durch sonische Düsen. Dies setzt voraus, dass der Brennstoff mit einem hinreichend hohen Druck geliefert wird, was auch in den meisten Fällen zutrifft oder bewerkstelligt werden kann. Diese Massnahme wirkt unabhängig von der Frequenz; jedoch kann man hierbei die Brennstoffmenge nicht über einen weiten Bereich variieren. Ein herkömmliches Regulierventil, das der Drosselung und der Mengeneinstellung dient, lässt sich bei einem Brenner üblicher Bauart nur ausserhalb des gesamten Brennersystems anbringen. In diesem Fall verbleibt aber zwischen Regulierventil und Brennkammereintritt immer noch ein Zuleitungssystem, das unter Umständen an einer Schwingung teilnehmen kann.
There are two main ways to combat such vibrations:
  • 1. By changing the acoustic properties, ie the impedances of the fuel supply line or the chamber. However, these measures only work in a certain frequency band, since the impedances depend on the frequency.
  • 2. By acoustic decoupling of the fuel supply system with an infinitely large entry impedance. This is achieved by severely restricting the fuel supply in the vicinity of the combustion chamber inlet, for example using sonic nozzles. This presupposes that the fuel is supplied at a sufficiently high pressure, which is also the case in most cases or can be accomplished. This measure works regardless of the frequency; however, the amount of fuel cannot be varied over a wide range. A conventional regulating valve, which is used for throttling and quantity adjustment, can only be fitted outside of the entire burner system in a burner of conventional design. In this case, however, there remains a supply system between the regulating valve and the combustion chamber inlet, which can possibly participate in an oscillation.

Aufgabe der Erfindung ist es, einen Brenner zu schaffen, der die oben beschriebene Abkopplung der Brennerstoffleitung zur Vermeidung von Brennkammerschwingungen mit der Möglichkeit der Brennstoffmengenregulierung in sich vereinigt.The object of the invention is to provide a burner which combines the above-described decoupling of the burner fuel line to avoid combustion chamber vibrations with the possibility of regulating the amount of fuel.

Erfindungsgemäss wird diese Aufgabe bei einer Brennstofflanze der eingangs-genannten Art mit den kennzeichnenden Merkmalen des Patentanspruchs 1 gelöst.According to the invention, this object is achieved in the case of a fuel lance of the type mentioned at the outset with the characterizing features of patent claim 1.

Der Vorteil der Erfindung ist im wesentlichen darin zu sehen, dass auf relativ einfache Weise eine Brennstofflanze geschaffen ist, die sowohl eine Abkopplung der Brennstoff-leitung zur Vermeidung von Brennkammerschwingungen als auch die Möglichkeit der Brennstoffmengenregulierung in kompakter Weise in sich vereinigt.The advantage of the invention can essentially be seen in the fact that a fuel lance is created in a relatively simple manner, which combines both a decoupling of the fuel line to avoid combustion chamber vibrations and the possibility of regulating the amount of fuel in a compact manner.

Die Entkoppelung wird insofern wirksam als durch diese kompakte Bauweise der Abstand zwischen Drosselkörper und Düsenaustritt wesentlich kürzer als die Wellenlänge typischer Eigenschwingungen des Brennkammersystems gehalten werden kann.The decoupling is effective insofar as the distance between the throttle body and Nozzle outlet can be kept much shorter than the wavelength of typical natural vibrations of the combustion chamber system.

Ein weiterer Vorteil der Erfindung ist darin zu sehen, dass die Brennstofflanze wahlweise mit zentralem oder radialem Düsenaustritt ausgestaltet werden kann.Another advantage of the invention can be seen in the fact that the fuel lance can optionally be designed with a central or radial nozzle outlet.

Bei der Zufuhr von vorgemischtem Brennstoff liegt ein zusätzlicher Vorteil darin, dass der Drosselkörper gleichzeitig als Flammen-Rückschlagsicherung wirkt.When premixed fuel is supplied, there is an additional advantage that the throttle body also acts as a flame arrester.

Im folgenden sind anhand der Zeichnung Ausführungsbeispiele des Erfindungsgegenstandes vereinfacht dargestellt und näher erläutert. Alle für das Verständnis der Erfindung unwesentlichen Elemente sind nicht dargestellt.Exemplary embodiments of the subject matter of the invention are shown in simplified form and explained in more detail below with reference to the drawing. All elements that are insignificant for understanding the invention are not shown.

Es zeigen:

  • Fig. 1 eine Brennstofflanze mit Zufuhr des Brennstoffes durch ein Innenrohr und zentralem Düsenaustritt;
  • Fig. 2 eine Brennstofflanze mit Zufuhr des Brennstoffes durch ein Innenrohr und radialem Düsenaustritt;
  • Fig. 3 eine Brennstofflanze mit Zufuhr des Brennstoffes durch das Lanzenrohr und zentralem Düsenaustritt;
  • Fig. 4 eine Brennstofflanze mit Zufuhr des Brennstoffes durch das Lanzenrohr und radialem Düsenaustritt.
Show it:
  • 1 shows a fuel lance with supply of the fuel through an inner tube and a central nozzle outlet;
  • 2 shows a fuel lance with supply of the fuel through an inner tube and radial nozzle outlet;
  • 3 shows a fuel lance with supply of the fuel through the lance tube and central nozzle outlet;
  • Fig. 4 shows a fuel lance with supply of fuel through the lance tube and radial nozzle outlet.

Fig. 1 zeigt stark vereinfacht die Konzeption einer Brennstofflanze 1, die Bestandteil eines nicht dargestellten Brenners ist, der seinerseits Bestandteil einer ebenfalls nicht dargestellten Brennkammer, z.B. einer Gasturbine ist. Beim Brenner kann es sich beispielsweise um einen Diffusionsbrenner mit verdrallter Luftzufuhr handeln.1 shows, in a highly simplified manner, the design of a fuel lance 1, which is part of a burner, not shown, which in turn is part of a combustion chamber, also not shown, for example a gas turbine. The burner can be, for example, a diffusion burner with a swirled air supply.

Die Brennstofflanze 1 besteht aus einem Lanzenrohr 2 mit einem zentralen Düsenaustritt 3. Stromaufwärts des Lanzenrohres 2 wird die Brennstofflanze 1 durch eine Büchse 4 gebildet, in der ein axial verstellbarer rohrförmiger Drosselkörper 5 geführt ist. Durch das Rohrinnere 6 findet die Zufuhr des Brennstoff 7 statt. Stromabwärtsseitig ist die Rohrwand 8 im ungeführten Teil des Drosselkörpers 5 in Umfangsrichtung und in axialer Richtung mit Brennstoffdurchtrittsöffnungen 9 versehen. Sowohl deren Anzahl als auch Anordnung ist beliebig; was die Form anbelangt, so können zum Beispiel Bohrungen oder Schlitze vorgesehen werden. Was die Zahl und Grösse der Brennstoffdurchtrittsöffnungen 9 anbelangt, so richten sich diese nach dem maximal erforderlichen Durchsatz des jeweiligen Brenners. Das Lanzenrohr 2 trägt im Rohrinnern einen Stempel 10, der mittels Stegen 11 - wie sie üblicherweise zur Abstützung von Innenkörpern bei durchströmten Querschnitten zum Einsatz gelangen - zentrisch zum Rohrinnern 6 des Drosselkörpers 5 gelagert ist. Eine ebenfalls dorthin plazierte Dichtung 12 sorgt dafür, dass die bei der jeweiligen axialen Position des Drosselkörpers 5 über dem Stempel 10 liegenden Brennstoffdurchtrittsöffnungen 9 gasdicht geschlossen sind. Die Gasdichtigkeit zwischen Drosselkörper 5 und Büchse 4 wird durch eine Dichtung 13 bewerkstelligt. Durch axiales Verschieben des Drosselkörpers 5 gegen den Stempel 10 kann der freie Querschnitt - d.h. die Anzahl der noch im Einsatz stehenden Brennstoffdurchtrittsöffnungen 9 - und damit die durchströmende Brennstoffmenge 7a verändert werden. Der freigegebene Strömungsquerschnitt hängt somit von der jeweiligen Eindringtiefe des Stempels 10 gegenüber dem Drosselkörper 5 ab. Wenn das Verhältnis des Brennstoffdruckes in der Zuleitung zum Druck am Düsenaustritt 3 einen kritischen Wert überschreitet, durchströmt der Brennstoff 7 die Brennstoffdurchtrittsöffnungen 9 im Drosselkörper 5 mit Schallgeschwindigkeit, so dass vom Düsenaustritt 3 stromauf laufende Druckstörungen den aus den Brennstoffdurchtrittsöffnungen 9 austretenden Brennstoffmenge 7a nicht mehr beeinflussen können. Konstruktiv ist es wichtig zu beachten, dass der Abstand zwischen Brennstoffdurchtrittsöffnungen 9 und Düsenaustritt 3 bzw. 15 wesentlich kürzer ist als die Wellenlänge typischer Eigenschwingungen des Brennkammersystems.The fuel lance 1 consists of a lance tube 2 with a central nozzle outlet 3. Upstream of the lance tube 2, the fuel lance 1 is formed by a bush 4 in which an axially adjustable tubular throttle body 5 is guided. The fuel 7 is supplied through the pipe interior 6. Downstream, the tube wall 8 in the unguided part of the throttle body 5 is provided with fuel passage openings 9 in the circumferential direction and in the axial direction. Both their number and arrangement are arbitrary; As far as the shape is concerned, holes or slots can be provided, for example. As far as the number and size of the fuel passage openings 9 are concerned, they depend on the maximum required throughput of the respective burner. The lance tube 2 carries a stamp 10 in the interior of the tube, which is mounted centrally to the tube interior 6 of the throttle body 5 by means of webs 11 - as are usually used to support inner bodies when cross-sections flow through. A seal 12 also placed there ensures that the fuel passage openings 9 located above the plunger 10 in the respective axial position of the throttle body 5 are closed gas-tight. The gas tightness between the throttle body 5 and the sleeve 4 is brought about by a seal 13. By axially displacing the throttle body 5 against the plunger 10, the free cross section - ie the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through can be changed. The released flow cross section thus depends on the respective penetration depth of the plunger 10 relative to the throttle body 5. If the ratio of the fuel pressure in the supply line to the pressure at the nozzle outlet 3 exceeds a critical value, the fuel 7 flows through the fuel passage openings 9 in the throttle body 5 at the speed of sound, so that pressure disturbances running upstream from the nozzle outlet 3 cause the pressure from the combustion Material passage openings 9 can no longer influence emerging fuel quantity 7a. In terms of design, it is important to note that the distance between fuel passage openings 9 and nozzle outlet 3 or 15 is considerably shorter than the wavelength of typical natural vibrations of the combustion chamber system.

In Fig. 2 ist, ähnlich wie in Fig. 1, ebenfalls eine stark vereinfachte Darstellung einer Brennstofflanze 1 dargestellt. Diese Ausführung ist gegenüber Fig. l durch den Unterschied gekennzeichnet, dass die durchströmende Brennstoffmenge 7a aus der Brennstofflanze 1 nunmehr radial austritt. Das Lanzenrohr 2 ist gleichbleibend zylindrisch und düsenaustrittsseitig offen. Der Stempel 10 wird über die Stege 11 verlängert und trägt an dessen Ende einen Zentralkörper 14. Die Oeffnung zwischen Ende des Lanzenrohres 2 und innenseitiger Auslaufkurve des Zentralkörpers 14 bildet den radialen Düsenaustritt 15.In FIG. 2, similar to FIG. 1, a greatly simplified illustration of a fuel lance 1 is also shown. This embodiment is distinguished from FIG. 1 by the difference that the fuel quantity 7a flowing through now emerges radially from the fuel lance 1. The lance tube 2 is continuously cylindrical and is open on the nozzle outlet side. The punch 10 is extended over the webs 11 and carries a central body 14 at its end. The opening between the end of the lance tube 2 and the inside runout curve of the central body 14 forms the radial nozzle outlet 15.

In Fig. 3 wird der Brennstoff 7 direkt durch die Brennstofflanze 1 zugeführt. Stromabwärts verläuft das Lanzenrohr 2 in eine bis zum zentralen Düsenaustritt 3 hin sich erstreckende Büchse 16 über. Der Drosselkörper 5 ist eine Spindel, die lediglich endseitig und nur auf einer bestimmten Länge rohrförmig ausgenommen ist. In dieser Partie sind auch die Brennstoffdurchtrittsöffnungen 9 angebracht. Der Innendurchmesser der Büchse 16 bildet zugleich die Oeffnung zum zentralen Düsenaustritt 3. Durch axiales Verschieben des Drosselkörpers 5 gegen die Büchse 16 kann der freie Querschnitt - d.h. die Anzahl der noch im Einsatz stehenden Brennstoffdurchtrittsöffnungen 9 - und damit die durchströmende Brennstoffmenge 7a verändert werden. Der Brennstoff 7 umströmt im Bereich des Lanzenrohres 2 den Drosselkörper 5. Dort wo das Lanzenrohr 2 in die Büchse 16 übergeht, durchströmt der Brennstoff jene Brennstoffdurchtrittsöffnungen 9, die auf Grund der Brennstoffmengenregulierung noch im Einsatz stehen, d.h. von der Büchse 16 noch nicht umhüllt sind. Im Gegensatz zu Fig. 1 und 2 strömt hier der Brennstoff 7 von aussen ins Innere des Drosselkörpers 5, um von hier aus zum Düsenaustritt 3 zu gelangen.In Fig. 3, the fuel 7 is fed directly through the fuel lance 1. Downstream the lance tube 2 runs into a bushing 16 which extends up to the central nozzle outlet 3. The throttle body 5 is a spindle which is only tubularly recessed at the end and only over a certain length. The fuel passage openings 9 are also provided in this section. The inner diameter of the sleeve 16 also forms the opening to the central nozzle outlet 3. By axially displacing the throttle body 5 against the sleeve 16, the free cross section - ie the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through can be changed. The fuel 7 flows around the throttle body 5 in the area of the lance tube 2. Where the lance tube 2 merges into the sleeve 16, the fuel flows through that combustion Substance passage openings 9, which are still in use due to the fuel quantity regulation, ie are not yet covered by the sleeve 16. In contrast to FIGS. 1 and 2, the fuel 7 flows from the outside into the interior of the throttle body 5 in order to reach the nozzle outlet 3 from here.

Fig. 4 zeigt ein beidseitig offenes Lanzenrohr 2, das in der Mitte durch eine Verengung 17 geteilt ist. Die Verengung erfüllt die gleiche Funktion wie die Büchse 16, beschrieben unter Fig. 3. Der Zentralkörper 14 ermöglicht einen radialen Düsenaustritt 15.Fig. 4 shows a lance tube 2 open on both sides, which is divided in the middle by a constriction 17. The constriction fulfills the same function as the bush 16, described under FIG. 3. The central body 14 enables a radial nozzle outlet 15.

Claims (4)

1. Brennstofflanze für die Zufuhr eines gasförmigen Brennstoffes oder eines Brennstoff-Luftgemisches in die Brennkammer einer Gasturbine, dadurch gekennzeichnet, dass die Brennstofflanze (1) einen inneren,gegenüber einem festen Körper (10, 16, 17) verstellbaren und mit Brennstoffdurchtrittsöffnungen (9) versehenen Drosselkörper (5) trägt, wobei die durchströmende Brennstoffmenge (7a) abhängig von der Eindringtiefe des Drosselkörpers (5) gegenüber dem festen Körper (10, 16, 17) ist.1. A fuel lance for the supply of a gaseous fuel or a fuel-air mixture into the combustion chamber of a gas turbine, characterized in that the fuel lance (1) has an inner, adjustable with respect to a solid body (10, 16, 17) and with fuel passage openings (9) provided throttle body (5), wherein the fuel quantity (7a) flowing through depends on the penetration depth of the throttle body (5) relative to the solid body (10, 16, 17). 2. Brennstofflanze nach Patentanspruch 1, dadurch gekennzeichnet, dass der Abstand zwischen Brennstoffdurchtrittsöffnungen (9) und Düsenaustritt (3, 15) kürzer ist als die Wellenlänge typischer Eigenschwingungen des Brennkammersystems.2. Fuel lance according to claim 1, characterized in that the distance between fuel passage openings (9) and nozzle outlet (3, 15) is shorter than the wavelength of typical natural vibrations of the combustion chamber system. 3. Brennstofflanze nach Patentanspruch 2, dadurch gekennzeichnet, dass der Düsenaustritt (3) zentral angeordnet ist.3. Fuel lance according to claim 2, characterized in that the nozzle outlet (3) is arranged centrally. 4. Brennstofflanze nach Patentanspruch 2, dadurch gekennzeichnet, dass der Düsenaustritt (15) radial in den Brennraum mündet.4. Fuel lance according to claim 2, characterized in that the nozzle outlet (15) opens radially into the combustion chamber.
EP84103522A 1983-04-13 1984-03-30 Fuel injector for the combustion chamber of a gas turbine Expired EP0122526B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1988/83 1983-04-13
CH198883 1983-04-13

Publications (2)

Publication Number Publication Date
EP0122526A1 true EP0122526A1 (en) 1984-10-24
EP0122526B1 EP0122526B1 (en) 1987-05-20

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EP84103522A Expired EP0122526B1 (en) 1983-04-13 1984-03-30 Fuel injector for the combustion chamber of a gas turbine

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US (1) US4761958A (en)
EP (1) EP0122526B1 (en)
JP (1) JPS59197736A (en)
DE (1) DE3463836D1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0394629A2 (en) * 1989-04-22 1990-10-31 Caldyn Apparatebau Gmbh Device for pulverising a fluid or for breaking up a gas into small bubbles
US5218824A (en) * 1992-06-25 1993-06-15 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
EP0571984A1 (en) * 1992-05-27 1993-12-01 Praxair Technology, Inc. Composite lance
EP0962699A2 (en) * 1998-05-30 1999-12-08 ROLLS-ROYCE plc A fuel injector
WO2000034714A1 (en) * 1998-12-08 2000-06-15 Siemens Aktiengesellschaft Combustion device and method for burning a fuel
WO2000034715A1 (en) * 1998-12-09 2000-06-15 Abb Alstom Power Uk Ltd. Modification of combustion reaction dynamics
EP1096201A1 (en) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Burner
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WO2000034714A1 (en) * 1998-12-08 2000-06-15 Siemens Aktiengesellschaft Combustion device and method for burning a fuel
US6615587B1 (en) 1998-12-08 2003-09-09 Siemens Aktiengesellschaft Combustion device and method for burning a fuel
WO2000034715A1 (en) * 1998-12-09 2000-06-15 Abb Alstom Power Uk Ltd. Modification of combustion reaction dynamics
EP1096201A1 (en) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Burner
WO2001033138A1 (en) * 1999-10-29 2001-05-10 Siemens Aktiengesellschaft Burner
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US9945725B2 (en) 2012-02-16 2018-04-17 Heimann Sensor Gmbh Thermopile infrared sensor structure with a high filling level

Also Published As

Publication number Publication date
JPS59197736A (en) 1984-11-09
EP0122526B1 (en) 1987-05-20
JPH0531050B2 (en) 1993-05-11
DE3463836D1 (en) 1987-06-25
US4761958A (en) 1988-08-09

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