EP1423647B1 - Combustion chamber arrangement - Google Patents

Combustion chamber arrangement Download PDF

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Publication number
EP1423647B1
EP1423647B1 EP02767441A EP02767441A EP1423647B1 EP 1423647 B1 EP1423647 B1 EP 1423647B1 EP 02767441 A EP02767441 A EP 02767441A EP 02767441 A EP02767441 A EP 02767441A EP 1423647 B1 EP1423647 B1 EP 1423647B1
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EP
European Patent Office
Prior art keywords
combustion chamber
turbine
individual
chamber arrangement
combustion chambers
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EP02767441A
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German (de)
French (fr)
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EP1423647A1 (en
Inventor
Peter Tiemann
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Siemens AG
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Siemens AG
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • the invention relates to a combustion chamber arrangement for a gas turbine with a plurality of opening in a common annular gap leading into a turbine chamber single combustion chambers, wherein the individual combustion chambers are upstream burner, which are connected to the individual combustion chambers through an outer housing.
  • the invention further relates to a gas turbine with such a combustion chamber arrangement.
  • Such combustion chamber arrangements for gas turbines are known in the art.
  • a mixture of an oxygen-containing fuel gas and a fuel ignited in the burners is burned in the combustion chambers and the expanding hot gases are diverted through the transition sections of the individual combustion chambers in the direction of the turbine chamber and the arrangement of vanes and blades therein.
  • the hot gas flows of circular cross-section generated in the usually circular-cylindrical constructed input sections of the individual combustion chambers are transferred through the transition sections into a hot gas flow with a circular-segment-shaped cross-section and finally combined to form a circular hot gas flow. This enters through the annular gap in the turbine chamber and drives the blades of the gas turbine.
  • Cooling fluid flows openly past the individual combustion chambers and causes a cooling effect.
  • the individual combustion chambers are designed with a simple wall, the cooling fluid flow is not directed and defined guided, resulting in an overall lower cooling efficiency.
  • such a design of the individual combustion chambers is structurally simpler and requires less effort.
  • the present invention seeks to further develop a combustion chamber arrangement of the type mentioned in that with structurally simple individual combustion chambers, the cooling efficiency can be significantly increased.
  • a cooling fluid can flow and cause a more effective convective cooling in this area due to the defined flow channel.
  • the single combustion chamber itself remains unchanged in its structure, a complication of the construction of the single combustion chamber itself is not required. In this way, the quasi closed cooled region of the single combustion chamber is extended into the interior of the turbine outer housing in the direction of the turbine space, the cooling efficiency is noticeably improved.
  • At least one tongue-like extension is formed on the neck, along a tangential to the annular gap, flattened side of the transition section of the single combustion chamber, leaving an intermediate space extend this.
  • the nozzle at the point where he collides with a nozzle for an adjacent single combustion chamber recesses the one substantially form dense transition to corresponding recesses of the adjacent nozzle.
  • the nozzle according to an advantageous embodiment of the invention may be formed closed in the circumferential direction of the single combustion chamber, so that over the entire peripheral region of the single combustion chamber in the section in which the nozzle according to the invention protrudes into the interior of the outer casing of the gas turbine quasi closed cooled.
  • the single combustion chamber is composed of a substantially cylindrically shaped, the burner downstream input section and a transition in a circular ring sector transition section, wherein the nozzle surrounds at least the input portion partially.
  • the inlet section is a thermally highly stressed element of the individual combustion chamber, so that the possibility of a quasi-closed cooling, which is provided in this area due to the neck provided according to the invention, results in a considerable improvement in the cooling of the Single combustion chamber with comparatively lower cost of cooling fluid represents.
  • a low cost of cooling fluid increases the overall cost of the gas turbine, and in cases where the cooling fluid is used simultaneously as fuel gas, the efficiency of the gas turbine is also increased.
  • the nozzle has a circular cross-sectional area and is arranged concentrically around the nikzylindrisch formed input section. This results in a uniform gap in the circumferential direction of the input section, which allows a uniform distribution of the cooling fluid flow and thus a uniform cooling in this area.
  • a gas turbine with a combustion chamber arrangement according to the previous embodiments is also the subject of the invention.
  • FIG. 1 shows a section of a gas turbine with a combustion chamber arrangement 1 according to the invention in a sectional view.
  • the combustion chamber assembly 1 is composed of a plurality of individual combustion chambers 3, which are arranged in a coronary manner and open into a common annular gap 13.
  • the annular gap 13 in turn opens into a turbine chamber 2, in which schematically indicated guide vanes and rotor blades of the turbine are located.
  • the individual combustion chambers 3 each burner 6 are connected upstream. These serve to ignite a mixture of an oxygen-containing fuel gas and a fuel, which burns in the individual combustion chambers 3 on.
  • the individual combustion chambers 3 are made up of an inlet section 4 adjoining the burner 6 and a transition section 5 which leads the inlet section 4 in the direction of the annular gap 13.
  • the burners 6 are connected to the individual combustion chambers 3 through a turbine outer housing 7. Starting from the turbine outer housing 7 in the direction of the turbine chamber 2, a nozzle 8 can be recognized, which extends concentrically around the circular cylindrical input section 4 of the single combustion chamber 3. Between the nozzle 8 and the input portion 4 of the single combustion chamber 3 while a gap space 9 is left, which can be traversed by a cooling fluid.
  • the ribs 10 are formed in the illustrated embodiment of the single combustion chamber 3, they However, they can also be formed on the neck 8 and extend in the direction of the single combustion chamber 3.
  • a recess 11 can be seen on the side of the nozzle 8, which is followed by an adjacent nozzle adjacent a single combustion chamber.
  • the individual combustion chambers are each arranged at an angle to one another.
  • the distance between the individual combustion chambers is reduced starting from the burner 6 in the direction of the annular gap 13, so that the cylindrical nozzle 8 abut each other in the direction of the annular gap 13 from a certain extent.
  • the recesses 11 are arranged in order to be able to extend the stubs 8 further in the direction of the annular gap 13 inwards.
  • adjacent sockets 8 abut each other and can be connected to each other for sealing, for example, welded, be.
  • the present invention arranged nozzle 8 form with its gap 9 a flow channel for a cooling fluid.
  • the quasi-closed in the flow channel guided cooling fluid due to the defined flow channel effectively contributes to a convective cooling of the individual combustion chambers 3 in the area covered by the nozzle 8 area.
  • tongue-like extensions 12a and 12b are further visible, which are guided while leaving a gap along the transition section 5 of the single combustion chamber 3.
  • These tongue-like extensions 12a and 12b represent an advantageous development of the invention, but are optional. They lead to a further enlargement of the quasi closed cooled region of the single combustion chamber 3 and thus to a further improvement of the cooling efficiency.
  • basic version of a combustion chamber arrangement according to the invention can be realized without the tongue-like extensions 12a and 12b only with the nozzle 8.
  • FIGS. 2 and 3 cutouts from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions.
  • FIGS. 2 and 3 cutouts from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions.
  • the different design variants with and without tongue-like extensions 12a and 12b only some of the single combustion chamber 3 at least in the input section 4 surrounding nozzle 8 with the tongue-like extension 12a and 12b shown.
  • the course of the flow 14 of a coolant fluid from the openly cooled region in the direction of the gaps under the tongue-like extensions 12a and subsequently below the connecting pieces 8 is shown in FIG.
  • the tongue-like extensions 12a and 12b taper in the direction of the outlet leading into the gap from the transition section 5 of the individual combustion chambers 3. This ensures a sufficiently large inlet surface for the cooling fluid flow.
  • combustion chamber arrangement 1 according to the invention a virtually closed-cooled region of the individual combustion chambers is created, in which cooling of the individual combustion chambers is possible with high efficiency.
  • the individual combustion chambers continue to be of simple construction, a complex double-walled design of the individual combustion chambers is not required.
  • the invention thus provides a simple means of providing a simple combustion chamber arrangement with the possibility of highly efficient cooling.

Abstract

The invention relates to a combustion chamber arrangement (1) for a gas turbine, with a number of individual combustion chambers (3) which open into an annular gap (13), leading to a turbine chamber (2), whereby burners (6) are arranged before the individual combustion chambers (3), connected to the individual combustion chambers (3) through a turbine housing (7). According to the invention, said combustion chamber arrangement may be further developed, such that the cooling efficiency of the individual combustion chambers may be significantly improved, with an embodiment of simple construction, whereby at least one collar (8), arranged on one side of the turbine housing (7), facing the turbine chamber, running radially in the direction of the turbine chamber (2), at least partly surrounds a section of at least one individual combustion chamber (3) whilst leaving a gap space (9).

Description

Die Erfindung betrifft eine Brennkammeranordnung für eine Gasturbine mit einer Vielzahl von in einem gemeinsamen, in einen Turbinenraum führenden Ringspalt mündenden Einzelbrennkammern, wobei den Einzelbrennkammern Brenner vorgeschaltet sind, die mit den Einzelbrennkammern durch ein Außengehäuse hindurch verbunden sind. Die Erfindung betrifft weiterhin eine Gasturbine mit einer solchen Brennkammeranordnung.The invention relates to a combustion chamber arrangement for a gas turbine with a plurality of opening in a common annular gap leading into a turbine chamber single combustion chambers, wherein the individual combustion chambers are upstream burner, which are connected to the individual combustion chambers through an outer housing. The invention further relates to a gas turbine with such a combustion chamber arrangement.

Derartige Brennkammeranordnungen für Gasturbinen sind im stand der Technik bekannt. Ein in den Brennern gezündetes Gemisch aus einem sauerstoffhaltigen Brenngas und einem Treibstoff wird in den Brennkammern verbrannt und die expandierenden Heißgase werden durch die Übergangsabschnitte der Einzelbrennkammern in Richtung des Turbinenraums und der darin befindlichen Anordnung aus Leitschaufeln und Laufschaufeln umgelenkt. Dabei werden die in den für gewöhnlich kreiszylindrisch aufgebauten Eingangsabschnitten der Einzelbrennkammern generierten Heißgasströme mit kreisförmigem Querschnitt durch die Übergangsabschnitte in einen Heißgasstrom mit kreisringsegmentförmigem Querschnitt überführt und schließlich zu einem kreisförmigen Heißgasstrom zusammengeführt. Dieser tritt durch den Ringspalt in den Turbinenraum ein und treibt die Laufschaufeln der Gasturbine an.Such combustion chamber arrangements for gas turbines are known in the art. A mixture of an oxygen-containing fuel gas and a fuel ignited in the burners is burned in the combustion chambers and the expanding hot gases are diverted through the transition sections of the individual combustion chambers in the direction of the turbine chamber and the arrangement of vanes and blades therein. In this case, the hot gas flows of circular cross-section generated in the usually circular-cylindrical constructed input sections of the individual combustion chambers are transferred through the transition sections into a hot gas flow with a circular-segment-shaped cross-section and finally combined to form a circular hot gas flow. This enters through the annular gap in the turbine chamber and drives the blades of the gas turbine.

Die bei der Verbrennung des Brenngas/Treibstoff-Gemisches freigesetzte Wärme führt zu einer stärken Erwärmung der Einzelbrennkammern, die eine intensive Kühlung in diesem Bereich erforderlich macht. Hierzu werden im Stand der Technik verschiedene Kühlprinzipien vorgeschlagen. Bei einer in der US 4,719,748 gezeigten Brennkammeranordnung ist die gesamte Einzelbrennkammer mit einem doppelschaligen Gehäuse ausgebildet, wobei zwischen den einzelnen Gehäuseschalen ein Luftspalt belassen ist. Durch Öffnungen in der äußeren Gehäuseschale strömt ein Kühlfluid in den zwischen den Gehäuseschalen belassenen Zwischenraum ein und prallt auf die innere Schale der Einzelbrennkammer auf. Hierbei wird bereits ein erster Kühlungseffekt bewirkt, welcher als Prahlkühlung bezeichnet wird. Im weiteren Verlauf durchströmt das Kühlfluid den zwischen den Gehäuseschalen belassenen Zwischenraum und sorgt für eine konvektive Kühlung. Dieses Konzept wird wegen der durchgehend zweischaligen Ausbildung der Brennkammerwandung auch als geschlossene Kühlung bezeichnet.The heat released during the combustion of the fuel gas / fuel mixture leads to a strong heating of the individual combustion chambers, which requires intensive cooling in this area. For this purpose, various cooling principles are proposed in the prior art. In a combustion chamber arrangement shown in US 4,719,748, the entire single combustion chamber is a double shell housing formed, wherein between the individual housing shells an air gap is left. Through openings in the outer housing shell, a cooling fluid flows into the space left between the housing shells and impinges on the inner shell of the single combustion chamber. In this case already a first cooling effect is effected, which is referred to as Prahlkühlung. In the further course, the cooling fluid flows through the space left between the housing shells and ensures convective cooling. This concept is also referred to as closed cooling because of the continuous two-shell design of the combustion chamber wall.

Ein anderes Konzept ist die sogenannte offene Kühlung, bei der die Einzelbrennkammern mit einer einfachen Wandung ausgebildet sind. Kühlfluid strömt offen an den Einzelbrennkammern vorbei und bewirkt einen Kühleffekt. Dadurch, daß die Einzelbrennkammern mit einer einfachen Wandung ausgestaltet sind, wird der Kühlfluidstrom nicht gerichtet und definiert geführt, was eine insgesamt geringere Kühleffizienz bewirkt. Andererseits ist eine solche Ausbildung der Einzelbrennkammern konstruktiv einfacher und bedingt einen geringeren Aufwand.Another concept is the so-called open cooling, in which the individual combustion chambers are formed with a simple wall. Cooling fluid flows openly past the individual combustion chambers and causes a cooling effect. Characterized in that the individual combustion chambers are designed with a simple wall, the cooling fluid flow is not directed and defined guided, resulting in an overall lower cooling efficiency. On the other hand, such a design of the individual combustion chambers is structurally simpler and requires less effort.

Aus dem jüngeren Stand der Technik ist es auch bekannt, Mischformen zwischen offener und geschlossener Kühlung bei den Einzelbrennkammern anzuwenden. Dabei werden die Einzelkammern über weite Bereiche offen gekühlt, lediglich in einem ein Außengehäuse durchragenden Bereich wird durch Anordnung einer zweiten, die erste Wandung unter Belassung eines Zwischenraumes umgebenden Wandung ein geschlossen zu kühlender Bereich geschaffen. Zwar sind bei diesem Konzept die verwendeten Einzelbrennkammern konstruktiv nach wie vor einfach gestaltet, jedoch ist der verbesserte Kühleffekt durch einen sehr kleinen quasi geschlossen gekühlten Bereich nicht so erheblich, wie es wünschenswert wäre.From the more recent state of the art, it is also known to apply mixed forms between open and closed cooling in the individual combustion chambers. In this case, the individual chambers are cooled open over wide areas, only in a region projecting through an outer housing a closed area to be cooled is created by arranging a second wall surrounding the first wall, leaving a gap therebetween. Although the single combustion chambers used in this concept are still structurally simple, the improved cooling effect is not as significant as would be desirable with a very small, virtually closed, cooled region.

Ausgehend von diesem Stand der Technik liegt der Erfindung die Aufgabe zugrunde, eine Brennkammeranordnung der eingangs genannten Art dahingehend weiterzuentwickeln, daß bei konstruktiv einfach gestalteten Einzelbrennkammern die Kühleffizienz erheblich gesteigert werden kann.Based on this prior art, the present invention seeks to further develop a combustion chamber arrangement of the type mentioned in that with structurally simple individual combustion chambers, the cooling efficiency can be significantly increased.

Zur Lösung dieser Aufgabe wird vorgeschlagen, bei einer Brennkammeranordnung der eingangs genannten Art zumindest einen an einer dem Turbinenraum zugewandten Seite des Turbinenaußengehäuses angeordneten, sich radial in Richtung des Turbinenraumes erstreckenden Stutzen vorzusehen, der einen Abschnitt zumindest einer Einzelbrennkammer unter Belassung eines Spaltraumes zumindest teilweise umgibt.To solve this problem, it is proposed that at least one arranged on a side facing the turbine chamber side of the turbine outer housing, to provide radially in the direction of the turbine chamber extending nozzle in a combustion chamber arrangement of the type mentioned at least partially surrounds a portion of at least one single combustion chamber leaving a gap.

Der am Turbinenaußengehäuse angeordnete, sich radial in Richtung des Turbinenraumes erstreckende mindestens eine Stutzen umgibt einen im Inneren des Turbinenaußengehäuses gelegene Abschnitt wenigstens einer Einzelbrennkammer und beläßt zwischen der Wandung der Einzelbrennkammer und dem Stutzen einen Spaltraum. In diesen Spaltraum kann ein Kühlfluid einströmen und aufgrund des definierten Strömungskanals eine effektivere konvektive Kühlung in diesem Bereich bewirken. Die Einzelbrennkammer selbst bleibt dabei unverändert einfach in ihrem Aufbau, eine Verkomplizierung der Konstruktion der Einzelbrennkammer selbst ist nicht erforderlich. Auf diese Weise wird der quasi geschlossen gekühlte Bereich der Einzelbrennkammer in das Innere des Turbinenaußengehäuses hinein in Richtung Turbinenraum verlängert, die Kühleffizienz wird spürbar verbessert.The arranged on the turbine outer housing, extending radially in the direction of the turbine chamber at least one nozzle surrounds a located in the interior of the turbine outer housing portion of at least one single combustion chamber and leaves between the wall of the single combustion chamber and the nozzle a gap. In this gap, a cooling fluid can flow and cause a more effective convective cooling in this area due to the defined flow channel. The single combustion chamber itself remains unchanged in its structure, a complication of the construction of the single combustion chamber itself is not required. In this way, the quasi closed cooled region of the single combustion chamber is extended into the interior of the turbine outer housing in the direction of the turbine space, the cooling efficiency is noticeably improved.

Um den Bereich mit einer quasi geschlossenen Kühlung noch weiter zu vergrößern, wird gemäß der Erfindung vorgeschlagen, daß an dem Stutzen mindestens eine zungenartige Verlängerung ausgebildet ist, die sich entlang einer bezüglich des Ringspaltes tangentialen, abgeflachten Seite des Übergangsabschnittes der Einzelbrennkammer unter Belassung eines Zwischenraumes zu diesem erstrecken. Durch die Anordnung einer derartigen Zunge wird das zur Kühlung verwendete Kühlfluid noch früher in einen definierten Raum gelenkt und kann effektiver zu einer konvektiven Kühlung der Einzelbrennkammer beitragen. Dabei ist es zur Schaffung eines ausreichenden Einströmbereiches in den Zwischenraum von Vorteil, wenn sich die an den Stutzen angeformte, zungenartige Verlängerung in Richtung des Ringspaltes bzw. des Turbinenraumes verjüngt.In order to further increase the area with a quasi-closed cooling, it is proposed according to the invention that at least one tongue-like extension is formed on the neck, along a tangential to the annular gap, flattened side of the transition section of the single combustion chamber, leaving an intermediate space extend this. By the Arrangement of such a tongue, the cooling fluid used for cooling is steered even earlier in a defined space and can contribute more effectively to a convective cooling of the single combustion chamber. It is to create a sufficient inflow into the space advantageous if the integrally formed on the neck, tongue-like extension tapers in the direction of the annular gap or the turbine chamber.

Um die erfindungsgemäß vorgesehenen Stutzen so weit wie möglich in Richtung des Turbinenraumes zu verlängern, wird gemäß einer vorteilhaften Weiterbildung der Erfindung vorgeschlagen, daß der Stutzen an der Stelle, an der er mit einem Stutzen für eine benachbarte Einzelbrennkammer zusammenstößt Ausnehmungen aufweist, die einen im wesentlichen dichten Übergang zu korrespondierenden Ausnehmungen des benachbarten Stutzens bilden.In order to extend the inventively provided nozzle as much as possible in the direction of the turbine chamber, it is proposed according to an advantageous embodiment of the invention that the nozzle at the point where he collides with a nozzle for an adjacent single combustion chamber recesses, the one substantially form dense transition to corresponding recesses of the adjacent nozzle.

Dabei kann der Stutzen gemäß einer vorteilhaften Weiterbildung der Erfindung in Umfangsrichtung der Einzelbrennkammer geschlossen ausgebildet sein, so daß sich über den gesamten Umfangsbereich der Einzelbrennkammer in dem Abschnitt, in dem der erfindungsgemäße Stutzen in das Innere des Außengehäuses der Gasturbine hineinragt quasi geschlossen gekühlt wird.In this case, the nozzle according to an advantageous embodiment of the invention may be formed closed in the circumferential direction of the single combustion chamber, so that over the entire peripheral region of the single combustion chamber in the section in which the nozzle according to the invention protrudes into the interior of the outer casing of the gas turbine quasi closed cooled.

Gemäß einer weiteren Weiterbildung der Erfindung setzt sich die Einzelbrennkammer aus einem im wesentlichen zylindrisch geformten, dem Brenner nachgeschalteten Eingangsabschnitt und einem in einen Kreisringsektor überblendenden Übergangsabschnitt zusammen, wobei der Stutzen zumindest den Eingangsabschnitt teilweise umgibt. Der Eingangsabschnitt ist wegen seiner Nähe zum Brenner ein thermisch besonders belastetes Element der Einzelbrennkammer, so daß die Möglichkeit einer quasi geschlossenen Kühlung, die aufgrund des erfindungsgemäß vorgesehenen Stutzens in diesem Bereich gegeben ist, eine erhebliche Verbesserung der Kühlung der Einzelbrennkammer mit vergleichsweise geringeren Aufwand an Kühlfluid darstellt. Ein geringer Aufwand an Kühlfluid steigert die Wirtschaftlichkeit der Gasturbine insgesamt, und in den Fällen, in denen das Kühlfluid gleichzeitig als Brenngas verwendet wird, wird zugleich die Effizienz der Gasturbine gesteigert. Bei einer kreiszylindrischen Ausbildung des Eingangsabschnittes ist gemäß einer weiteren Weiterbildung der Erfindung vorgesehen, daß der Stutzen eine kreisförmige Querschnittsfläche aufweist und konzentrisch um dem kreiszylindrisch ausgebildeten Eingangsabschnitt angeordnet ist. So ergibt sich ein in Umfangsrichtung des Eingangsabschnittes gleichmäßiger Spaltraum, welcher eine gleichmäßige Verteilung des Kühlfluidstroms und damit eine gleichmäßige Kühlung in diesem Bereich ermöglicht.According to a further development of the invention, the single combustion chamber is composed of a substantially cylindrically shaped, the burner downstream input section and a transition in a circular ring sector transition section, wherein the nozzle surrounds at least the input portion partially. Because of its proximity to the burner, the inlet section is a thermally highly stressed element of the individual combustion chamber, so that the possibility of a quasi-closed cooling, which is provided in this area due to the neck provided according to the invention, results in a considerable improvement in the cooling of the Single combustion chamber with comparatively lower cost of cooling fluid represents. A low cost of cooling fluid increases the overall cost of the gas turbine, and in cases where the cooling fluid is used simultaneously as fuel gas, the efficiency of the gas turbine is also increased. In a circular cylindrical design of the input portion is provided according to a further development of the invention that the nozzle has a circular cross-sectional area and is arranged concentrically around the kreiszylindrisch formed input section. This results in a uniform gap in the circumferential direction of the input section, which allows a uniform distribution of the cooling fluid flow and thus a uniform cooling in this area.

Eine Gasturbine mit einer Brennkammeranordnung gemäß den vorigen Ausführungen ist ebenfalls Gegenstand der Erfindung.A gas turbine with a combustion chamber arrangement according to the previous embodiments is also the subject of the invention.

Weitere Vorteile und Merkmale der Erfindung ergeben sich aus den nachfolgend geschilderten Ausführungsbeispielen anhand der beigefügten Zeichnungen. In den Zeichnungen zeigen:

Fig. 1
in geschnittener Ansicht einen Abschnitt einer Gasturbine mit einer erfindungsgemäßen Brennkammeranordnung,
Fig. 2
in perspektivischer Darstellung einen Ausschnitt aus einer erfindungsgemäßen Brennkammeranordnung, gesehen aus Richtung des Turbinenraumes, wobei einige der gezeigten erfindungsgemäßen Stutzen gemäß einem alternativen Ausführungsbeispiel mit zungenartigen Verlängerungen versehen sind, und
Fig. 3
in perspektivischer Darstellung einen Ausschnitt aus einer erfindungsgemäßen Brennkammeranordnung, gesehen aus Richtung der Brenner, wobei einige der gezeigten, erfindungsgemäßen Stutzen mit zungenartigen Verlängerungen ausgebildet sind.
Further advantages and features of the invention will become apparent from the following described embodiments with reference to the accompanying drawings. In the drawings show:
Fig. 1
in section a section of a gas turbine with a combustion chamber arrangement according to the invention,
Fig. 2
in perspective view a section of a combustion chamber arrangement according to the invention, as seen from the direction of the turbine chamber, wherein some of the inventive nozzle shown are provided according to an alternative embodiment with tongue-like extensions, and
Fig. 3
in perspective view a section of a combustion chamber arrangement according to the invention, as seen from the direction of the burner, wherein some of shown, nozzle according to the invention are formed with tongue-like extensions.

In den Figuren sind gleiche Elemente mit gleichen Bezugszeichen versehen.In the figures, the same elements are provided with the same reference numerals.

In Figur 1 ist in geschnittener Ansicht ein Ausschnitt aus einer Gasturbine mit einer erfindungsgemäßen Brennkammeranordnung 1 eingezeigt. Die Brennkammeranordnung 1 setzt sich zusammen aus einer Vielzahl von Einzelbrennkammern 3, welche kranzartig angeordnet sind und in einem gemeinsamen Ringspalt 13 münden. Der Ringspalt 13 wiederum mündet in einem Turbinenraum 2, in welchem sich schematisch angedeutete Leitschaufeln und Laufschaufeln der Turbine befinden.FIG. 1 shows a section of a gas turbine with a combustion chamber arrangement 1 according to the invention in a sectional view. The combustion chamber assembly 1 is composed of a plurality of individual combustion chambers 3, which are arranged in a coronary manner and open into a common annular gap 13. The annular gap 13 in turn opens into a turbine chamber 2, in which schematically indicated guide vanes and rotor blades of the turbine are located.

Den Einzelbrennkammern 3 sind jeweils Brenner 6 vorgeschaltet. Diese dienen der Zündung eines Gemisches aus einem sauerstoffhaltigen Brenngas und einem Treibstoff, welches in den Einzelbrennkammern 3 weiter verbrennt. Die Einzelbrennkammern 3 setzen sich dabei aus einem sich an den Brenner 6 anschließenden Eingangsabschnitt 4 und einem den Eingangsabschnitt 4 in Richtung des Ringspaltes 13 überleitenden Übergangsabschnitt 5 zusammen. Die Brenner 6 sind mit den Einzelbrennkammern 3 durch ein Turbinenaußengehäuse 7 hindurch verbunden. Ausgehend von dem Turbinenaußengehäuse 7 in Richtung des Turbinenraums 2 kann ein Stutzen 8 erkannt werden, welcher sich konzentrisch um den kreiszylinderisch ausgebildeten Eingangsabschnitt 4 der Einzelbrennkammer 3 erstreckt. Zwischen dem Stutzen 8 und dem Eingangsabschnitt 4 der Einzelbrennkammer 3 ist dabei ein Spaltraum 9 belassen, welcher von einem Kühlfluid durchströmt werden kann. An dem Eingangsabschnitt 4 der Einzelbrennkammer 3 sind dabei entlang des Umfangs verteilt Rippen 10 angeformt, mit welchen sich die Einzelbrennkammer 3 an dem Stutzen 8 abstützt. Die Rippen 10 sind im gezeigten Ausführungsbeispiel an der Einzelbrennkammer 3 angeformt, sie können jedoch auch an dem Stutzen 8 angeformt sein und sich in Richtung der Einzelbrennkammer 3 erstrecken.The individual combustion chambers 3 each burner 6 are connected upstream. These serve to ignite a mixture of an oxygen-containing fuel gas and a fuel, which burns in the individual combustion chambers 3 on. The individual combustion chambers 3 are made up of an inlet section 4 adjoining the burner 6 and a transition section 5 which leads the inlet section 4 in the direction of the annular gap 13. The burners 6 are connected to the individual combustion chambers 3 through a turbine outer housing 7. Starting from the turbine outer housing 7 in the direction of the turbine chamber 2, a nozzle 8 can be recognized, which extends concentrically around the circular cylindrical input section 4 of the single combustion chamber 3. Between the nozzle 8 and the input portion 4 of the single combustion chamber 3 while a gap space 9 is left, which can be traversed by a cooling fluid. At the input section 4 of the single combustion chamber 3 are distributed along the circumference ribs 10 are formed, with which the single combustion chamber 3 is supported on the nozzle 8. The ribs 10 are formed in the illustrated embodiment of the single combustion chamber 3, they However, they can also be formed on the neck 8 and extend in the direction of the single combustion chamber 3.

Eine Ausnehmung 11 ist an der Seite des Stutzens 8 zu erkennen, an welcher sich ein benachbarter Stutzen einer nebenliegenden Einzelbrennkammer anschließt. Um die Einzelbrennkammern 3 in einen gemeinsamen Ringspalt 13 zu überführen, sind die Einzelbrennkammern jeweils unter einem Winkel zueinander angeordnet. Dadurch wird der Abstand zwischen den Einzelbrennkammern ausgehend von dem Brenner 6 in Richtung des Ringspaltes 13 verringert, so daß die zylinderförmigen Stutzen 8 ab einer bestimmten Erstreckung in Richtung des Ringspaltes 13 aneinander stoßen. An dieser Stelle sind die Ausnehmungen 11 angeordnet, um die Stutzen 8 noch weiter in Richtung des Ringspaltes 13 nach innen verlängern zu können. Entlang des Randes der Ausnehmungen 11 liegen benachbarte Stutzen 8 aneinander an und können zur Abdichtung miteinander verbunden, beispielsweise verschweißt, sein.A recess 11 can be seen on the side of the nozzle 8, which is followed by an adjacent nozzle adjacent a single combustion chamber. In order to transfer the individual combustion chambers 3 into a common annular gap 13, the individual combustion chambers are each arranged at an angle to one another. As a result, the distance between the individual combustion chambers is reduced starting from the burner 6 in the direction of the annular gap 13, so that the cylindrical nozzle 8 abut each other in the direction of the annular gap 13 from a certain extent. At this point, the recesses 11 are arranged in order to be able to extend the stubs 8 further in the direction of the annular gap 13 inwards. Along the edge of the recesses 11 adjacent sockets 8 abut each other and can be connected to each other for sealing, for example, welded, be.

Die erfindungsgemäß angeordneten Stutzen 8 bilden mit ihrem Spaltraum 9 einen Strömungskanal für ein Kühlfluid. Das in dem Strömungskanal quasi geschlossen geführte Kühlfluid trägt aufgrund des definierten Strömungskanals effektiv zu einer konvektiven Kühlung der Einzelbrennkammern 3 in den von dem Stutzen 8 überdeckten Bereich bei.The present invention arranged nozzle 8 form with its gap 9 a flow channel for a cooling fluid. The quasi-closed in the flow channel guided cooling fluid due to the defined flow channel effectively contributes to a convective cooling of the individual combustion chambers 3 in the area covered by the nozzle 8 area.

In Figur 1 sind weiterhin zwei einander gegenüberliegende, tangential bezüglich des Ringspalts 13 verlaufende zungenartige Verlängerungen 12a und 12b zu erkennen, die unter Belassung eines Spaltraumes entlang des Übergangsabschnittes 5 der Einzelbrennkammer 3 geführt sind. Diese zungenartige Verlängen 12a und 12b stellen eine vorteilhafte Weiterbildung der Erfindung dar, sind jedoch optional. Sie führen zu einer weiteren Vergrößerung des quasi geschlossen gekühlten Bereichs der Einzelbrennkammer 3 und damit zu einer weiteren Verbesserung der Kühleffizienz. Eine Grundversion einer erfindungsgemäßen Brennkammeranordnung kann jedoch ohne die zungenartigen Verlängerungen 12a und 12b lediglich mit den Stutzen 8 verwirklicht werden.In Figure 1, two opposing tangential with respect to the annular gap 13 extending tongue-like extensions 12a and 12b are further visible, which are guided while leaving a gap along the transition section 5 of the single combustion chamber 3. These tongue-like extensions 12a and 12b represent an advantageous development of the invention, but are optional. They lead to a further enlargement of the quasi closed cooled region of the single combustion chamber 3 and thus to a further improvement of the cooling efficiency. A However, basic version of a combustion chamber arrangement according to the invention can be realized without the tongue-like extensions 12a and 12b only with the nozzle 8.

In den Figuren 2 sowie 3 sind perspektivisch aus unterschiedlichen Blickrichtungen Ausschnitte aus erfindungsgemäß ausgebildeten Brennkammeranordnungen gezeigt. Dabei sind zur Verdeutlichung der unterschiedlich Ausgestaltungsvarianten mit und ohne zungenartige Verlängerungen 12a bzw. 12b nur einige der die Einzelbrennkammer 3 zumindest im Eingangsabschnitt 4 umgebenden Stutzen 8 mit den zungenartigen Verlängerung 12a bzw. 12b dargestellt. In Figur 2 ist darüber hinaus mit Hilfe von Pfeilen der Verlauf der Strömung 14 eines Kühlmittelfluids aus dem offen gekühlten Bereich in Richtung der Spalträume unterhalb der zungenartigen Verlängerungen 12a und nachfolgend unterhalb der Stutzen 8 dargestellt. Zu erkennen ist auch, daß die zungenartigen Verlängerungen 12a bzw. 12b sich in Richtung des in den Spaltraum überleitenden Austrittes aus den Übergangsabschnitt 5 der Einzelbrennkammern 3 hin verjüngen. Hierdurch wird eine ausreichend große Eintrittsfläche für den Kühlfluidstrom gewährleistet.In FIGS. 2 and 3, cutouts from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions. In this case, to illustrate the different design variants with and without tongue-like extensions 12a and 12b, only some of the single combustion chamber 3 at least in the input section 4 surrounding nozzle 8 with the tongue-like extension 12a and 12b shown. In addition, the course of the flow 14 of a coolant fluid from the openly cooled region in the direction of the gaps under the tongue-like extensions 12a and subsequently below the connecting pieces 8 is shown in FIG. It can also be seen that the tongue-like extensions 12a and 12b taper in the direction of the outlet leading into the gap from the transition section 5 of the individual combustion chambers 3. This ensures a sufficiently large inlet surface for the cooling fluid flow.

Zu erkennen ist, daß mit der erfindungsgemäßen Brennkammeranordnung 1 ein quasi geschlossen gekühlter Bereich der Einzelbrennkammern geschaffen wird, in welchem eine Kühlung der Einzelbrennkammern mit hoher Effizienz möglich ist. Dabei sind die Einzelbrennkammern weiterhin von einfacher Konstruktion, eine aufwendige doppelwandige Ausführung der Einzelbrennkammern ist nicht erforderlich. Mit der Erfindung wird so ein einfaches Mittel angegeben, eine einfache Brennkammeranordnung mit der Möglichkeit einer hoch effizienten Kühlung zu schaffen.It can be seen that with the combustion chamber arrangement 1 according to the invention a virtually closed-cooled region of the individual combustion chambers is created, in which cooling of the individual combustion chambers is possible with high efficiency. The individual combustion chambers continue to be of simple construction, a complex double-walled design of the individual combustion chambers is not required. The invention thus provides a simple means of providing a simple combustion chamber arrangement with the possibility of highly efficient cooling.

Claims (8)

  1. Combustion chamber arrangement for a gas turbine with a plurality of individual combustion chambers (3) which open into a common annular gap (13) transitioning into a turbine chamber (2), whereby burners (6) are arranged ahead of the individual combustion chambers (3), connected to the individual combustion chambers (3) through a turbine outer housing (7), whereby a collar (8) running radially in the direction of the turbine chamber (2) is arranged on the side of the turbine outer housing (7) facing the turbine chamber (2), enclosing a section of at least one of the individual combustion chambers (3) at least partially leaving a gap space (9),
    wherein
    there is a tongue-like extension (12a, 12b) configured on the collar (8), which extension projects beyond a flattened side of the transition section (5) that is tangential in respect of the annular gap leaving a gap space.
  2. Combustion chamber arrangement according to claim 1, wherein the at least one collar (8) is configured in a closed manner in the circumferential direction of the individual combustion chamber (3).
  3. Combustion chamber arrangement according to one of claims 1 or 2, wherein the individual combustion chamber (3) comprises an essentially cylindrical inlet section (4) arranged after the burner (6) and a transition section (5) merging into a circular-sector-shaped cross-section, whereby the collar (8) at least partially encloses at least the inlet section (4).
  4. Combustion chamber arrangement according to claim 3, wherein the inlet section (4) is configured cylindrically and the collar (8) has a circular cross-sectional area and is arranged concentrically around the inlet section (4).
  5. Combustion chamber arrangement according to claim 1, wherein the tongue-like extension (12a, 12b) is configured to taper in the direction of the annular gap (13).
  6. Combustion chamber arrangement according to one of claims 1 to 5, wherein the collars (8) have lateral recesses (11) in the area in which they meet collars (8) arranged around adjacent individual combustion chambers (3), along which recesses the adjacent collars (8) are in contact with each other in an essentially sealing manner.
  7. Combustion chamber arrangement according to claim 6, wherein the adjacent collars are connected together along the edges of the recesses (11).
  8. Gas turbine characterised by a combustion chamber arrangement (1) according to one of claims 1 to 7.
EP02767441A 2001-09-03 2002-08-27 Combustion chamber arrangement Expired - Fee Related EP1423647B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02767441A EP1423647B1 (en) 2001-09-03 2002-08-27 Combustion chamber arrangement

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EP01121089A EP1288574A1 (en) 2001-09-03 2001-09-03 Combustion chamber arrangement
EP01121089 2001-09-03
EP02767441A EP1423647B1 (en) 2001-09-03 2002-08-27 Combustion chamber arrangement
PCT/EP2002/009556 WO2003021149A1 (en) 2001-09-03 2002-08-27 Combustion chamber arrangement

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EP1423647A1 EP1423647A1 (en) 2004-06-02
EP1423647B1 true EP1423647B1 (en) 2006-07-26

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EP02767441A Expired - Fee Related EP1423647B1 (en) 2001-09-03 2002-08-27 Combustion chamber arrangement

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US20040237500A1 (en) 2004-12-02
EP1288574A1 (en) 2003-03-05
JP2005502020A (en) 2005-01-20
WO2003021149A1 (en) 2003-03-13
US6968672B2 (en) 2005-11-29
CN1537212A (en) 2004-10-13
DE50207662D1 (en) 2006-09-07
EP1423647A1 (en) 2004-06-02

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