EP0841517B1 - Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle - Google Patents

Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle Download PDF

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Publication number
EP0841517B1
EP0841517B1 EP97114341A EP97114341A EP0841517B1 EP 0841517 B1 EP0841517 B1 EP 0841517B1 EP 97114341 A EP97114341 A EP 97114341A EP 97114341 A EP97114341 A EP 97114341A EP 0841517 B1 EP0841517 B1 EP 0841517B1
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EP
European Patent Office
Prior art keywords
fuel
nozzle
cooling liquid
injection device
tube
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EP97114341A
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German (de)
French (fr)
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EP0841517A3 (en
EP0841517A2 (en
Inventor
William Kwan
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication of EP0841517A2 publication Critical patent/EP0841517A2/en
Publication of EP0841517A3 publication Critical patent/EP0841517A3/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • 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
    • F23D2214/00—Cooling

Definitions

  • the invention relates to a fuel injection device for a gas turbine combustion chamber with a liquid-cooled injector that a Has fuel guide tube with a surrounding coolant tube, which near the nozzle outlet opening in an annular space for the Coolant flows out or this directly surrounding the fuel guide tube Annulus forms.
  • a Has fuel guide tube with a surrounding coolant tube which near the nozzle outlet opening in an annular space for the Coolant flows out or this directly surrounding the fuel guide tube Annulus forms.
  • Liquid-cooled fuel injectors are particularly popular tiered gas turbine combustors are used, in which a so-called Main burner is temporarily switched off.
  • a coolant preferably fuel
  • this injector directed, d. H. into a wall area of the injection nozzle and of course without getting into the combustion chamber - returned again, which intensively cools the injection nozzle.
  • the two The first-mentioned documents show such fuel injection devices with such liquid-cooled injectors, but these are fuel injectors relatively complex.
  • the coolant tube directly and the fuel guide tube via an elbow in a nozzle holder are stored, one in the coolant tube in the nozzle holder provided first coolant line and in the hollow angle piece a fuel supply line opens.
  • FIG. 1 shows a section through a fuel injection device according to the invention is shown.
  • Fig. 2 shows the view X on the so-called.
  • 3 the view X of the angle piece which will be explained later
  • FIG. 4 shows the section A-A from FIG. 1.
  • the fuel injector shown projects with its entirety with 1 designated injection nozzle into the combustion chamber, not shown ner gas turbine into it.
  • the injection nozzle 1 is on a so-called Nozzle carrier 2 of the fuel injector attached.
  • a fuel supply line 3 which into a in the injection nozzle 1 provided fuel guide tube 4 passes.
  • the latter opens into a cavity 5 within a nozzle tip element 6, which has at least one nozzle outlet opening 7, via which the Fuel supplied via the feed line 3 and the guide tube 4 can get into the combustion chamber of the gas turbine.
  • an end cap 8 is provided as usual, inside of which the fuel guide tube 4 is mounted.
  • the nozzle tip element 6 and the end cap 8 or the Area thereof is to be cooled to prevent fuel, which is in this area in the guide tube 4, coked. Due to the high temperatures inside a gas turbine combustor namely in particular the area located near the nozzle outlet opening 7 an injector 1 such high temperatures that in the injector 1 Coke any fuel that is no longer being pumped would.
  • coolant is now through the Injector 1 out u. a. through an annular space 9, which u. a. of the end cap 8 and the outside of the fuel guide tube 4 limited becomes. Coolant is guided through this annular space 9, specifically according to the arrows, which are provided with the reference number 15 elsewhere are, and fuel is preferably used again as the cooling liquid is coming.
  • a coolant tube 10 is provided in the same from the annular space 9, which surrounds the fuel guide tube 4 at a distance.
  • the Upper space segment 12a can supply coolant to the annular space 9 and are discharged again via the lower space segment 12b become.
  • the upper space segment 12a has a feed channel 13 and the lower space segment 12b with a discharge channel 14 for each Coolant connected.
  • the coolant flow is indicated by arrows 15 shown.
  • Both the feed channel 13 and the discharge channel 14 naturally run also inside the nozzle holder 2 and are inside it essentially designed as coolant lines, which with the same reference numerals, namely 13, 14 are provided.
  • the second coolant line 14 also surrounds a distance the fuel supply line 13 and is substantially concentric arranged to this. This is the second via an outlet opening 17 Coolant line 14 with a discharge flange provided on the nozzle carrier 2 18 connected for coolant. With its other end it ends this coolant line 14 is provided in a directly in the nozzle holder 2 Discharge channel 14, and is bypassed via this discharge channel 14 a so-called angle piece 19 connected to the lower space segment 12b.
  • the angle piece 19 just mentioned serves on the one hand to accommodate the End cap 8 opposite end of the fuel guide tube 4 and connects, since it is hollow, this fuel guide tube 4 at the same time with the fuel supply line 3.
  • the elbow 19 in Nozzle carrier 2 stored or pressed in as shown.
  • the fuel injection device described is characterized by the elements mentioned through a particularly simple structure.
  • the corresponding shaped nozzle carrier 2 which is divided in the area of level 20 can be formed, both the coolant lines 13 and 14 and the fuel supply line 3 are simply used.
  • the elbow 19 can be used, which is the lower end the coolant line 14 leads. Then you can in this elbow 19 the fuel guide tube 4 are inserted, after which the partition element 11 and the coolant tube 10 are used.
  • only the end cap 8, with the nozzle tip element 6, and a shielding cap 21 can be mounted.
  • the space segments 12a, 12b here take the form of cylinder segments after the fuel guide tube 4 is straight.
  • a particularly simple shape of the partition element 11 whereby by a suitable choice of its cross-sectional area also that the cheapest volume or the cheapest contour of the room segments 12a, 12b is adjustable.
  • a seal carrier 22 is also provided, which has ring seals 23 is provided, in particular around an undesired outflow of cooling liquid to prevent in an area away from the discharge flange 18.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Description

Die Erfindung betrifft eine Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse, die ein ein Kraftstoff-Führungsrohr mit Abstand umgebendes Kühlflüssigkeits-Rohr aufweist, welches nahe der Düsen-Austrittsöffnung in einen Ringraum für die Kühlflüssigkeit mündet oder diesen das Kraftstoff-Führungsrohr direkt umgebenden Ringraum bildet. Zum technischen Umfeld wird neben der EP 0 689 006 A1 und der WO 94/08179 insbesondere auf die FR 2 166 395 A verwiesen.The invention relates to a fuel injection device for a gas turbine combustion chamber with a liquid-cooled injector that a Has fuel guide tube with a surrounding coolant tube, which near the nozzle outlet opening in an annular space for the Coolant flows out or this directly surrounding the fuel guide tube Annulus forms. In addition to the EP 0 689 006 A1 and WO 94/08179 in particular to the FR 2 166 395 A.

Flüssigkeitsgekühlte Kraftstoff-Einspritzdüsen kommen insbesondere bei gestuften Gasturbinen-Brennkammem zum Einsatz, bei welchen ein sog. Hauptbrenner zeitweise abgeschaltet ist. Um zu verhindern, daß die in der Einspritzdüse auch bei deren Abschaltung befindliche Kraftstoffmenge durch die hohen Temperaturen, die eine derartige in die Gasturbinen-Brennkammer hineinragende Einspritzdüse annehmen kann, verkokt, wird eine Kühlflüssigkeit, und zwar bevorzugt Kraftstoff, durch diese Einspritzdüse geleitet, d. h. in einen Wandbereich der Einspritzdüse hineingeführt und-selbstverständlich ohne in die Brennkammer zu gelangen - wieder zurückgeführt, wodurch eine intensive Kühlung der Einspritzdüse erfolgt. Die beiden oben erstgenannten Schriften zeigen solche Kraftstoffeinspritzvorrichtungen mit derartigen flüssiggekühlten Einspritzdüsen, jedoch sind diese Kraftstoffeinspritzvorrichtungen relativ bauaufwendig. Liquid-cooled fuel injectors are particularly popular tiered gas turbine combustors are used, in which a so-called Main burner is temporarily switched off. To prevent that in the Injector even when the fuel quantity is switched off the high temperatures such in the gas turbine combustor protruding injection nozzle can be coked a coolant, preferably fuel, through this injector directed, d. H. into a wall area of the injection nozzle and of course without getting into the combustion chamber - returned again, which intensively cools the injection nozzle. The two The first-mentioned documents show such fuel injection devices with such liquid-cooled injectors, but these are fuel injectors relatively complex.

Eine hinsichtlich der Strömungsverhältnisse der Kühlflüssigkeit günstigere Kraftstoffeinspritzvorrichtung, bei der innerhalb des Kühlflüssigkeits-Rohres bezüglich der Kraftstoff-Strömungsrichtung stromauf des Ringraumes ein das Kraftstoff-Führungsrohr umgebendes Trennwand-Element vorgesehen ist, welches den Innenraum des Kühlflüssigkeits-Rohres in zwei Raumsegmente unterteilt, wobei das erste Raumsegment mit einem Zuführkanal und das zweite Raumsegment mit einem Abführkanal für die Kühlflüssigkeit verbunden ist, zeigt die FR 2 166 395 A.One more favorable with regard to the flow conditions of the coolant Fuel injector inside the coolant pipe with respect to the fuel flow direction upstream of the annulus the partition wall element surrounding the fuel guide tube is provided is which divides the interior of the coolant pipe into two room segments divided, the first space segment with a feed channel and the second space segment is connected to a discharge channel for the coolant FR 2 166 395 A.

Wie nun eine Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einem derartige Trennwand-Element nach der letztgenannten Schrift versehen werden kann und dabei in günstiger Weise montierbar aufgebaut werden kann, wenn die Düsen-Austrittsöffnung abseits und winkelig zur Achse der im Düsenträger verlaufenden Kraftstoff-Zuführleitung liegt, soll mit der vorliegenden Erfindung aufgezeigt werden (= Aufgabe der Erfindung).How a fuel injection device for a gas turbine combustion chamber can now be provided with such a partition element according to the last-mentioned document and can be constructed so that it can be assembled in a favorable manner if the nozzle outlet opening lies apart and at an angle to the axis of the fuel supply line running in the nozzle carrier , is to be demonstrated with the present invention (= object of the invention).

Zur Lösung dieser Aufgabe ist vorgesehen, daß das Kühlflüssigkeits-Rohr direkt und das Kraftstoff-Führungsrohr über ein Winkelstück in einem Düsenträger gelagert sind, wobei im Kühlflüssigkeits-Rohr eine im Düsenträger vorgesehene erste Kühlflüssigkeits-Leitung und im hohl ausgebildeten Winkelstück eine Kraftstoff-Zuführleitung mündet.To solve this problem it is provided that the coolant tube directly and the fuel guide tube via an elbow in a nozzle holder are stored, one in the coolant tube in the nozzle holder provided first coolant line and in the hollow angle piece a fuel supply line opens.

Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche. Näher erläutert wird die Erfindung anhand eines bevorzugten Ausführungsbeispieles, wobei in Fig. 1 ein Schnitt durch eine erfindungsgemäße Kraftstoffeinspritzvorrichtung dargestellt ist. Fig. 2 zeigt die Ansicht X auf den sog. Düsenträger, Fig. 3 die Ansicht X auf das später noch erläuterte Winkelstück, und Fig. 4 den Schnitt A-A aus Fig. 1.Advantageous training and further education are included in the subclaims. The invention is explained in more detail with reference to a preferred exemplary embodiment, 1 shows a section through a fuel injection device according to the invention is shown. Fig. 2 shows the view X on the so-called. 3 the view X of the angle piece which will be explained later, and FIG. 4 shows the section A-A from FIG. 1.

Die gezeigte Kraftstoffeinspritzvorrichtung ragt mit ihrer in ihrer Gesamtheit mit 1 bezeichneten Einspritzdüse in die nicht dargestellte Brennkammer ei ner Gasturbine hinein. Wie üblich ist die Einspritzdüse 1 dabei an einem sog. Düsenträger 2 der Kraftstoffeinspritzvorrichtung befestigt. Innerhalb dieses Düsenträgers 2 verläuft eine Kraftstoff-Zuführleitung 3, die in ein in der Einspritzdüse 1 vorgesehenes Kraftstoff-Führungsrohr 4 übergeht. Letzeres mündet in einem Hohlraum 5 innerhalb eines Düsen-Spitzenelementes 6, welches zumindest eine Düsen-Austrittsöffnung 7 aufweist, über welche der über die Zuführleitung 3 sowie das Führungsrohr 4 herangeführte Kraftstoff in den Brennraum der Gasturbine gelangen kann. Innerhalb des Düsen-Spitzenelementes 6 ist dabei wie üblich eine Endkappe 8 vorgesehen, innerhalb derer das Kraftstoff-Führungsrohr 4 gelagert ist.The fuel injector shown projects with its entirety with 1 designated injection nozzle into the combustion chamber, not shown ner gas turbine into it. As usual, the injection nozzle 1 is on a so-called Nozzle carrier 2 of the fuel injector attached. Within this Nozzle carrier 2 runs a fuel supply line 3, which into a in the injection nozzle 1 provided fuel guide tube 4 passes. The latter opens into a cavity 5 within a nozzle tip element 6, which has at least one nozzle outlet opening 7, via which the Fuel supplied via the feed line 3 and the guide tube 4 can get into the combustion chamber of the gas turbine. Inside the nozzle tip element 6, an end cap 8 is provided as usual, inside of which the fuel guide tube 4 is mounted.

Insbesondere das Düsen-Spitzenelement 6 sowie die Endkappe 8 bzw. der Bereich derselben soll gekühlt werden, um zu verhindem, daß Kraftstoff, welcher in diesem Bereich im Führungsrohr 4 steht, verkokt. Aufgrund der hohen Temperaturen im Inneren einer Gasturbinen-Brennkammer nimmt nämlich insbesondere der nahe der Düsen-Austrittsöffnung 7 liegende Bereich einer Einspritzdüse 1 derart hohe Temperaturen an, daß in der Einspritzdüse 1 befindlicher, nicht weiter geförderter Kraftstoff zwangsläufig verkoken würde.In particular the nozzle tip element 6 and the end cap 8 or the Area thereof is to be cooled to prevent fuel, which is in this area in the guide tube 4, coked. Due to the high temperatures inside a gas turbine combustor namely in particular the area located near the nozzle outlet opening 7 an injector 1 such high temperatures that in the injector 1 Coke any fuel that is no longer being pumped would.

Zur Kühlung des genannten Bereiches wird nun Kühlflüssigkeit durch die Einspritzdüse 1 geführt und zwar u. a. durch einen Ringraum 9, der u. a. von der Endkappe 8 sowie der Außenseite des Kraftstoff-Führungsrohres 4 begrenzt wird. Durch diesen Ringraum 9 wird Kühlflüssigkeit geführt, und zwar gemäß den Pfeilen, die an anderer Stelle mit der Bezugsziffer 15 versehen sind, und wobei als Kühlflüssigkeit bevorzugt abermals Kraftstoff zum Einsatz kommt.To cool the area mentioned, coolant is now through the Injector 1 out u. a. through an annular space 9, which u. a. of the end cap 8 and the outside of the fuel guide tube 4 limited becomes. Coolant is guided through this annular space 9, specifically according to the arrows, which are provided with the reference number 15 elsewhere are, and fuel is preferably used again as the cooling liquid is coming.

Sowohl für die Zuführung von Kühlflüssigkeit in als auch für die Abführung derselben aus dem Ringraum 9 ist ein Kühlflüssigkeits-Rohr 10 vorgesehen, welches das Kraftstoff-Führungsrohr 4 mit Abstand umgibt. Dabei ist der Ringraum zwischen dem Kühlflüssigkeits-Rohr 10 und dem Kraftstoff-Führungsrohr 4 durch ein sog. Trennwand-Element 11 in zwei Raumsegmente 12a, 12b unterteilt, wie insbesondere aus Fig. 4 hervorgeht. Über das obere Raumsegment 12a kann dabei Kühlflüssigkeit in den Ringraum 9 zugeführt werden, und über das untere Raumsegment 12b wieder abgeführt werden. Hierfür ist das obere Raumsegment 12a mit einem Zuführkanal 13 und das untere Raumsegment 12b mit einem Abführkanal 14 jeweils für Kühlflüssigkeit verbunden. Der Kühlflüssigkeitsstrom ist dabei durch Pfeile 15 dargestellt.Both for the supply of coolant as well as for the discharge a coolant tube 10 is provided in the same from the annular space 9, which surrounds the fuel guide tube 4 at a distance. Here is the Annulus between the coolant tube 10 and the fuel guide tube 4 by a so-called partition element 11 in two room segments 12a, 12b divided, as can be seen in particular from FIG. 4. About the Upper space segment 12a can supply coolant to the annular space 9 and are discharged again via the lower space segment 12b become. For this purpose, the upper space segment 12a has a feed channel 13 and the lower space segment 12b with a discharge channel 14 for each Coolant connected. The coolant flow is indicated by arrows 15 shown.

Sowohl der Zuführkanal 13 als auch der Abführkanal 14 verlaufen selbstverständlich auch innerhalb des Düsenträgers 2 und sind innerhalb dessen im wesentlichen als Kühlflüssigkeits-Leitungen ausgebildet, welche mit den gleichen Bezugsziffern, nämlich 13, 14 versehen sind. Die erste Kühlflüssigkeitsleitung 13, die sich im wesentlichen an einen am Düsenträger 2 vorgesehenen Zuführflansch 16 anschließt, mündet als Rohrstück direkt im oberen Raumsegment 12a. Die zweite Kühlflüsigkeitsleitung 14 umgibt ebenfalls mit einem Abstand die Kraftstoff-Zuführleitung 13 und ist im wesentlichen konzentrisch zu dieser angeordnet. Über eine Austrittsöffnung 17 ist diese zweite Kühlflüssigkeitsleitung 14 mit einem am Düsenträger 2 vorgesehenen Abführflansch 18 für Kühlflüssigkeit verbunden. Mit ihrem anderen Ende mündet diese Kühlflüssigkeitsleitung 14 in einem direkt im Düsenträger 2 vorgesehenen Abführkanal 14, und ist über diesen Abführkanal 14 unter Umgehung eines sog. Winkelstückes 19 mit dem unteren Raumsegment 12b verbunden.Both the feed channel 13 and the discharge channel 14 naturally run also inside the nozzle holder 2 and are inside it essentially designed as coolant lines, which with the same reference numerals, namely 13, 14 are provided. The first coolant line 13, which are essentially provided on a nozzle holder 2 Feed flange 16 connects, opens as a pipe section directly in the upper Room segment 12a. The second coolant line 14 also surrounds a distance the fuel supply line 13 and is substantially concentric arranged to this. This is the second via an outlet opening 17 Coolant line 14 with a discharge flange provided on the nozzle carrier 2 18 connected for coolant. With its other end it ends this coolant line 14 is provided in a directly in the nozzle holder 2 Discharge channel 14, and is bypassed via this discharge channel 14 a so-called angle piece 19 connected to the lower space segment 12b.

Das soeben genannte Winkelstück 19 dient einerseits zur Aufnahme des der Endkappe 8 abgewandten Endes des Kraftstoff-Führungsrohres 4 und verbindet, da es hohl ausgebildet ist, dieses Kraftstoff-Führungsrohr 4 gleichzeitig mit der Kraftstoff-Zuführleitung 3. Seinerseits ist das Winkelstück 19 im Düsenträger 2 wie gezeigt gelagert bzw. eingepreßt.The angle piece 19 just mentioned serves on the one hand to accommodate the End cap 8 opposite end of the fuel guide tube 4 and connects, since it is hollow, this fuel guide tube 4 at the same time with the fuel supply line 3. In turn, the elbow 19 in Nozzle carrier 2 stored or pressed in as shown.

Mit den genannten Elementen zeichnet sich die beschriebene Kraftstoffeinspritzvorrichtung durch einen besonders einfachen Aufbau aus. In den entsprechend geformten Düsenträger 2, der im Bereich der Ebene 20 geteilt ausgebildet sein kann, können sowohl die Kühlflüssigkeits-Leitungen 13 und 14 als auch die Kraftstoff-Zuführleitung 3 einfach eingesetzt werden. Ebenso einfach ist das Winkelstück 19 einsetzbar, welches dabei das untere Ende der Kühlflüssigkeitsleitung 14 führt. Anschließend kann in dieses Winkelstück 19 das Kraftstoff-Führungsrohr 4 eingesteckt werden, wonach das Trennwand-Element 11 und das Kühlflüssigkeits-Rohr 10 eingesetzt werden. Schließlich muß nur noch die Endkappe 8, mit dem Düsen-Spitzenelement 6, sowie eine Abschirmkappe 21 montiert werden. Trotz dieses einfachen Aufbaus ist eine optimale Führung der Kühlflüssigkeit möglich, wobei sich durch die Zuführung in den Ringraum 9 lediglich im oberen Bereich desselben und durch die Abführung der Kühlflüssigkeit lediglich im unteren Bereich des Ringraumes 9 eine optimale Kühlflüssigkeitsströmung mit günstigster Wärmeabfuhr einstellt. Selbstverständlich kann die Kühlflüssigkeitsströmung auch entgegen der Pfeilrichtung 15 erfolgen.The fuel injection device described is characterized by the elements mentioned through a particularly simple structure. In the corresponding shaped nozzle carrier 2, which is divided in the area of level 20 can be formed, both the coolant lines 13 and 14 and the fuel supply line 3 are simply used. As well simply the elbow 19 can be used, which is the lower end the coolant line 14 leads. Then you can in this elbow 19 the fuel guide tube 4 are inserted, after which the partition element 11 and the coolant tube 10 are used. Finally, only the end cap 8, with the nozzle tip element 6, and a shielding cap 21 can be mounted. Despite this simple structure an optimal guidance of the coolant is possible, whereby the supply into the annular space 9 only in the upper area thereof and by removing the coolant only in the lower area of the Annulus 9 an optimal coolant flow with the cheapest heat dissipation sets. Of course, the coolant flow also take place in the opposite direction of the arrow 15.

Die Raumsegmente 12a, 12b nehmen hier die Form von Zylindersegmenten an, nachdem das Kraftstoff-Führungsrohr 4 geradlinig verläuft. Hiermit ergibt sich auch eine besonders einfache Formgebung des Trennwand-Elementes 11, wobei durch geeignete Wahl von dessen Querschnittsfläche auch das jeweils günstigste Volumen bzw. die jeweils günstigste Kontur der Raumsegmente 12a, 12b einstellbar ist. Im oberen Bereich des Düsenträgers 2 ist ferner noch ein Dichtungsträger 22 vorgesehen, der mit Ringdichtungen 23 versehen ist, insbesondere um ein unerwünschtes Abströmen von Kühlflüssigkeit in einen Bereich abseits des Abführflansches 18 zu verhindern. The space segments 12a, 12b here take the form of cylinder segments after the fuel guide tube 4 is straight. Hereby results also a particularly simple shape of the partition element 11, whereby by a suitable choice of its cross-sectional area also that the cheapest volume or the cheapest contour of the room segments 12a, 12b is adjustable. In the upper area of the nozzle holder 2 is a seal carrier 22 is also provided, which has ring seals 23 is provided, in particular around an undesired outflow of cooling liquid to prevent in an area away from the discharge flange 18.

Kommt als Kühlflüssigkeit Kraftstoff zum Einsatz, so kann über diesen Abführflansch 18 die abgeführte Kühlflüssigkeit bzw. der abgeführte Kraftstoff im übrigen einer weiteren Einspritzdüse für einen stets betriebenen Pilotbrenner der Gasturbinen-Brennkammer zugeführt werden. Es ist aber auch möglich, den Kraftstoff zurück in den Tank zu leiten. Daneben können selbstverständlich eine Vielzahl von Details insbesondere konstruktiver Art durchaus abweichend vom gezeigten Ausführungsbeispiel gestaltet sein, ohne den Inhalt der Patentansprüche zu verlassen. So muß die Düsen-Austrittsöffnung 7, bzw. mehrere davon, die ringförmig angeordnet sein können, auch nicht wie hier gestaltet sein, sondern es kann mit einer einzigen Austrittsöffnung 7 auch ein konisch geformter einziger Kraftstoffstrahl erzeugt werden.If fuel is used as the coolant, this can be done via this discharge flange 18 the removed coolant or the removed fuel otherwise a further injection nozzle for a pilot burner that is always operated be fed to the gas turbine combustor. It is also possible to return the fuel to the tank. Next to it of course, a variety of details, particularly of a constructive nature be completely different from the exemplary embodiment shown, without leaving the content of the claims. So the nozzle outlet must 7, or several of them, which can be arranged in a ring, also not be designed as here, but it can be done with one Outlet opening 7 also produces a conically shaped single fuel jet become.

Claims (4)

  1. Fuel injection device for a gas turbine combustion chamber with a liquid-cooled injection nozzle (1) which features a cooling liquid tube (10) remotely surrounding a fuel feed tube (4) which connects to an annulus (9) for the cooling liquid near the nozzle orifice jet (7) or which forms said annulus (9) directly surrounding the fuel feed tube (4), where a partition (11) is arranged within the cooling liquid tube (10) upstream of the annulus (9) relative to the direction of fuel flow, said partition (11) dividing the interior of the cooling liquid tube (10) into two space segments (12a, 12b), with the first space segment (12a) connecting to an inlet duct (13) and the second space segment (12b) connecting to an outlet duct (14) for the cooling liquid,
    characterized in that the nozzle jet orifice (7) is arranged remotely from and at an angle to the axis of the fuel supply line (3) extending in the nozzle holder (2) and that the cooling liquid tube (10) is supported directly and the fuel feed tube (4) by means of an elbow (19) in the a nozzle holder (2), with a first cooling liquid line (13) provided in the nozzle holder (2) connecting to the cooling liquid tube (10) and with a fuel supply line (3) connecting to the hollow-type elbow (19).
  2. Fuel injection device in accordance with Claim 1, characterized in that the fuel supply line (3) provided in the nozzle holder (2) is surrounded by a second cooling liquid line (14).
  3. Fuel injection device in accordance with Claim 1 or 2, characterized in that the nozzle holder (2) features a supply fitting (16) and a discharge fitting (18) for cooling liquid of which each is connected to one of the cooling liquid lines (13, 14).
  4. Fuel injection device in accordance with one of the preceding Claims,
    characterized in that the annulus (9) near the nozzle jet orifice (7) is limited by an end cap (8) provided in the nozzle tip element (6) at least in the direction of the nozzle jet orifice (7).
EP97114341A 1996-11-07 1997-08-20 Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle Expired - Lifetime EP0841517B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19645961 1996-11-07
DE19645961A DE19645961A1 (en) 1996-11-07 1996-11-07 Fuel injector for a gas turbine combustor with a liquid cooled injector

Publications (3)

Publication Number Publication Date
EP0841517A2 EP0841517A2 (en) 1998-05-13
EP0841517A3 EP0841517A3 (en) 1998-12-23
EP0841517B1 true EP0841517B1 (en) 2001-12-19

Family

ID=7810954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97114341A Expired - Lifetime EP0841517B1 (en) 1996-11-07 1997-08-20 Fuel injection device for a gas turbine combustion chamber with a liquid cooled injection nozzle

Country Status (4)

Country Link
US (1) US6003781A (en)
EP (1) EP0841517B1 (en)
CA (1) CA2220213C (en)
DE (2) DE19645961A1 (en)

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Also Published As

Publication number Publication date
DE59705876D1 (en) 2002-01-31
CA2220213C (en) 2006-04-04
DE19645961A1 (en) 1998-05-14
EP0841517A3 (en) 1998-12-23
EP0841517A2 (en) 1998-05-13
CA2220213A1 (en) 1998-05-07
US6003781A (en) 1999-12-21

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