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EP0122526B1 - 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
EP0122526B1
EP0122526B1 EP84103522A EP84103522A EP0122526B1 EP 0122526 B1 EP0122526 B1 EP 0122526B1 EP 84103522 A EP84103522 A EP 84103522A EP 84103522 A EP84103522 A EP 84103522A EP 0122526 B1 EP0122526 B1 EP 0122526B1
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EP
European Patent Office
Prior art keywords
fuel
combustion chamber
nozzle outlet
lance
burner
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.)
Expired
Application number
EP84103522A
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German (de)
French (fr)
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EP0122526A1 (en
Inventor
Laan Dr. Hellat
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.)
BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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Filing date
Publication date
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Publication of EP0122526A1 publication Critical patent/EP0122526A1/en
Application granted granted Critical
Publication of EP0122526B1 publication Critical patent/EP0122526B1/en
Expired legal-status Critical Current

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Classifications

    • 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 burner with a fuel lance according to the preamble of claim 1.
  • the burner consists of a fixed gas line which is integrated in a mixing tube which can be moved by rotation.
  • This manual rotation of the mixing tube simultaneously and inevitably regulates the gas outlet cross section in the gas line and the air inlet cross section in the mixing tube.
  • the outlet cross-section for the mixture formed from gas and air is also regulated.
  • the regulation of the gas outlet cross-section takes place in that a displaceable sleeve encasing the gas line releases the desired gas passage cross-section.
  • the gas passage cross section consists of a number of gas passage holes distributed axially and over the circumference of the gas line.
  • the aim is not to restrict the fuel supply in the vicinity of the combustion chamber inlet, nor can one speak of sonic nozzles for the fuel supply, which only enable the fuel supply system to be decoupled acoustically.
  • the fuel quantity cannot be regulated over a wide range, which means that the burner described in DE-C-330 857 could only be used in a combustion chamber with a narrow power range.
  • the object of the invention is to provide a burner with a fuel lance, which enables the above-described decoupling of the burner fuel line to avoid combustion chamber vibrations, with the further possibility of being able to guarantee the fuel quantity regulation over a wide range.
  • the advantage of the invention can be seen essentially in the fact that a burner 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 fuel quantity over a wide range in a compact manner.
  • the decoupling is effective insofar as this compact design enables the distance between the throttle body and the nozzle outlet to be kept significantly shorter than the wavelength of typical settling 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.
  • Fig. 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, e.g. 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 tube 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.
  • the lance tube 2 carries a stamp 10 inside the tube, which is centered on the tube interior 6 of the throttle body 5 by means of webs 11 - as they are usually used for supporting internal bodies with cross-sections flowing through them.
  • 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 bush 4 is brought about by a seal 13.
  • the free cross section - i.e. the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through - are 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 no longer influence the fuel quantity 7a emerging from the fuel passage openings 9 can.
  • 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 those fuel passage openings 9 which are still in use due to the fuel quantity regulation, i.e. are not yet encased 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 bushing 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)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft einen Brenner mit einer Brennstofflanze gemäss Oberbegriff des Anspruchs 1.The invention relates to a burner with a fuel lance according to the preamble of claim 1.

Bei herkömmlichen Brennkammern, die mit einem gasförmigen Brennstoff betrieben werden, findet die Regulierung der Brennstoffmenge - von der Flammenfront in der Brennkammer ausgesehen - weiter stromaufwärts statt, d.h., zwischen Mengenregulierung und Entzündungsebene des gasförmigen Brennstoffes oder eines Brennstoff/Luft-Gemisches entsteht stets eine mehr oder weniger lange Gassäule, die Ursache ist, dass es in der Brennkammer zu selbsterregten Schwingungen kommen kann. Die Modulation des in die Brennkammer eingedusten gasförmigen Brennstoffes oder eines Brennstoff/Luft-Gemisches, wie beispielsweise aus DE-A-22 27 281 entnommen werden kann, beruht auf Druckschwankungen in der Düsenebene. Der für die Selbsterregung notwendige Rückkopplungskreis ist dann geschlossen, wenn die von den Zufuhrschwankungen bewirkten Aenderungen des Brennstoffumsatzes in der Flammenebene mit dem Brennkammerdruck eine Phasenbedingung erfüllen. Ein klassisches Beispiel hierfür ist die sogenannte "singende Flamme".In conventional combustion chambers which are operated with a gaseous fuel, the regulation of the fuel quantity - from the flame front in the combustion chamber - takes place further upstream, i.e. there is always more between the quantity regulation and the level of ignition of the gaseous fuel or a fuel / air mixture or less long gas column, the cause is that self-excited vibrations can occur in the combustion chamber. The modulation of the gaseous fuel or a fuel / air mixture injected into the combustion chamber, as can be seen for example from DE-A-22 27 281, is based on pressure fluctuations in the nozzle plane. The feedback loop necessary for self-excitation is closed when the changes in the fuel conversion caused by the supply fluctuations in the flame level meet a phase condition with the combustion 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 Inpedanzen der Brennstoffzuleitung oder der Brennkammer. 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 unabhänig 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 combustion 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 independently 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 under certain circumstances can participate in an oscillation.

In DE-C-330 857 besteht der Brenner aus einer feststehenden Gasleitung, die in ein durch Drehung verschiebbares Mischrohr integriert ist. Durch diese manuelle Drehung des Mischrohres wird gleichzeitig und zwangsläufig der Gasaustrittsquerschnitt in der Gasleitung und der Lufteintrittsquerschnitt in das Mischrohr geregelt. Darüber hinaus wird auch der Austrittsquerschnitt für das aus Gas und Luft gebildete Gemisch geregelt. Die Regelung des Gasaustrittsquerschnittes geschieht, indem eine verschiebbare, die Gasleitung ummantelnde Muffe den erwünschten Gasdurchtrittsquerschnitt freigibt.In DE-C-330 857 the burner consists of a fixed gas line which is integrated in a mixing tube which can be moved by rotation. This manual rotation of the mixing tube simultaneously and inevitably regulates the gas outlet cross section in the gas line and the air inlet cross section in the mixing tube. In addition, the outlet cross-section for the mixture formed from gas and air is also regulated. The regulation of the gas outlet cross-section takes place in that a displaceable sleeve encasing the gas line releases the desired gas passage cross-section.

Zwar geht aus dieser Druckschrift hervor, dass der Gasdurchtrittsquerschnitt aus einer Anzahl axial und über den Umfang der Gasleitung verteilte Gasdurchtrittsbohrungen besteht. Indessen wird hier keine starke Drosselung der Brennstoffzufuhr in der Nähe des Brennkammereintritts angestrebt, noch kann man hier von sonischen Düsen bei der Brennstoffzufuhr sprechen, die erst eine akustische Abkopplung des Brennstoffzufuhrsystems ermöglichen. Hier besteht also die Gefahr, dass von der Brennkammer aus, selbst wenn diese unmittelbar dem Brenner nachgeschaltet wäre, eine akustische Rückkopplung über die nicht sonischen Düsen auf die Brenngasleitung stattfinden kann. Darüber hinaus lässt sich mit dem hier vorgeschlagenen Gasaustrittsquerschnitt keine Regulierung der Brennstoffmenge über einen weiten Bereich erzielen, wodurch der Einsatz des in DE-C-330 857 beschriebenen Brenners allenfalls nur bei Brennkammer mit einer schmalen Leistungsbreite zum Einsatz kommen könnte.It is clear from this publication that the gas passage cross section consists of a number of gas passage holes distributed axially and over the circumference of the gas line. In the meantime, the aim is not to restrict the fuel supply in the vicinity of the combustion chamber inlet, nor can one speak of sonic nozzles for the fuel supply, which only enable the fuel supply system to be decoupled acoustically. There is therefore a risk here that, even if it were connected directly downstream of the burner, there would be an acoustic feedback from the combustion chamber via the non-sonic nozzles to the fuel gas line. In addition, with the gas outlet cross section proposed here, the fuel quantity cannot be regulated over a wide range, which means that the burner described in DE-C-330 857 could only be used in a combustion chamber with a narrow power range.

Aufgabe der Erfindung ist es, einen Brenner mit einer Brennstofflanze zu schaffen, der die oben beschriebene Abkopplung der Brennerstoffleitung zur Vermeidung von Brennkammerschwingungen ermöglicht, mit der weiteren Möglichkeit, die Brennstoffmengenregulierung über einen weiten Bereich gewährleisten zu können.The object of the invention is to provide a burner with a fuel lance, which enables the above-described decoupling of the burner fuel line to avoid combustion chamber vibrations, with the further possibility of being able to guarantee the fuel quantity regulation over a wide range.

Erfindungsgemäss wird diese Aufgabe, bei einem Brenner der eingangs genannten Art, mit den kennzeichnenden Merkmalen des Patentanspruchs 1 gelöst.According to the invention, this object is achieved in a burner 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 ein Brenner geschaffen ist, der sowohl eine Abkopplung der Brennstoffleitung zur Vermeidung von Brennkammerschwingungen als auch die Möglichkeit der Brennstoffmengenregulierung über einen weiten Bereich in kompakter Weise in sich vereinigt.The advantage of the invention can be seen essentially in the fact that a burner 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 fuel quantity over a wide range in a compact manner.

Die Entkopplung wird insofern wirksam, als durch diese kompakte Bauweise der Abstand zwischen Drosselkörper und Düsenaustritt wesentlich kürzer als die Wellenlänge typscher Eingeschwingungen des Brennakmmersystems gehalten werden kann.The decoupling is effective insofar as this compact design enables the distance between the throttle body and the nozzle outlet to be kept significantly shorter than the wavelength of typical settling 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 not essential 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 druch 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. 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 Innen körpern 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.Fig. 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, e.g. 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 tube 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 inside the tube, which is centered on the tube interior 6 of the throttle body 5 by means of webs 11 - as they are usually used for supporting internal bodies with cross-sections flowing through them. 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 bush 4 is brought about by a seal 13. By axially displacing the throttle body 5 against the plunger 10, the free cross section - i.e. the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through - are 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 no longer influence the fuel quantity 7a emerging from the fuel passage openings 9 can. 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. 1 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 - i.e. the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through - are 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 those fuel passage openings 9 which are still in use due to the fuel quantity regulation, i.e. are not yet encased 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 bushing 16, described under FIG. 3. The central body 14 enables a radial nozzle outlet 15.

Claims (3)

1. Burner with a fuel lance for feeding a gaseous fuel or a fuel/air mixture into the combustion chamber of a gas turbine, characterized in that the fuel lance (1) carries an internal restrictor (5) which is axially adjustable relative to a solid body (10, 16, 17), this restrictor being provided on the downstream side with a number of fuel passage orifices (9) pointing to the nozzle outlet (3, 15), and the fuel rate (7a) which, under more than supercritical pressure conditions, flows at sonic velocity through the fuel passage orifices (9) depends on the depth of penetration of the restrictor (5) relative to the solid body (10, 16, 17) in the region of the fuel passage orifices (9), the distance of which from the nozzle outlet (3, 15) is substantially smaller than the havelength of typical resonant vibrations of the combustion chamber system.
2. Burner according to Patent Claim 1, characterized in that the nozzle outlet (3) is arranged centrally.
3. Burner according to Patent Claim 1, characterized in that the nozzle outlet (15) leads 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
CH198883 1983-04-13
CH1988/83 1983-04-13

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EP0122526A1 EP0122526A1 (en) 1984-10-24
EP0122526B1 true 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)

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Also Published As

Publication number Publication date
DE3463836D1 (en) 1987-06-25
JPS59197736A (en) 1984-11-09
US4761958A (en) 1988-08-09
EP0122526A1 (en) 1984-10-24
JPH0531050B2 (en) 1993-05-11

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