EP1423647A1 - Combustion chamber arrangement - Google Patents

Combustion chamber arrangement

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Publication number
EP1423647A1
EP1423647A1 EP02767441A EP02767441A EP1423647A1 EP 1423647 A1 EP1423647 A1 EP 1423647A1 EP 02767441 A EP02767441 A EP 02767441A EP 02767441 A EP02767441 A EP 02767441A EP 1423647 A1 EP1423647 A1 EP 1423647A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbine
individual combustion
individual
chamber arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02767441A
Other languages
German (de)
French (fr)
Other versions
EP1423647B1 (en
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP02767441A priority Critical patent/EP1423647B1/en
Publication of EP1423647A1 publication Critical patent/EP1423647A1/en
Application granted granted Critical
Publication of EP1423647B1 publication Critical patent/EP1423647B1/en
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Classifications

    • 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 individual combustion chambers opening into a common annular gap leading into a turbine space, the individual combustion chambers being preceded by burners which are connected to the individual combustion chambers through an outer casing.
  • the invention further relates to a gas turbine with such a combustion chamber arrangement.
  • Combustion chamber arrangements of this type for gas turbines are known in the prior 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 deflected by the transition sections of the individual combustion chambers in the direction of the turbine chamber and the arrangement of guide vanes and rotor blades located therein.
  • the hot gas streams with a circular cross-section generated in the usually circular-cylindrical inlet sections of the individual combustion chambers are converted through the transition sections into a hot gas stream with a cross-section in the form of an annular segment and finally brought together to form a circular hot gas stream. This enters the turbine space through the annular gap and drives the blades of the gas turbine.
  • Cooling fluid flows openly past the individual combustion chambers and creates a cooling effect. Because the individual combustion chambers are designed with a simple wall, the cooling fluid flow is not directed and defined, which results in a lower overall cooling efficiency. On the other hand, such a design of the individual combustion chambers is structurally simpler and requires less effort.
  • the individual chambers are cooled openly over wide areas, only in an area projecting through an outer housing is a closed area to be cooled created by arranging a second wall surrounding the first wall while leaving an intermediate space.
  • the individual combustion chambers used in this concept are still structurally simple, the improved cooling effect due to a very small quasi-closed cooled area is not as significant as would be desirable. Proceeding from this prior art, the invention is based on the task of further developing a combustion chamber arrangement of the type mentioned at the outset in such a way that the cooling efficiency can be increased considerably in the case of individual combustion chambers of simple design.
  • the at least one nozzle which is arranged on the turbine outer housing and extends radially in the direction of the turbine chamber, surrounds a section of at least one individual combustion chamber located in the interior of the turbine outer housing and leaves a gap between the wall of the individual combustion chamber and the nozzle.
  • a cooling fluid can flow into this gap space and, due to the defined flow channel, can effect a more effective convective cooling in this area.
  • the structure of the individual combustion chamber itself remains simple, and the design of the individual combustion chamber itself is not complicated. In this way, the quasi-closed, cooled region of the individual combustion chamber is extended into the interior of the turbine outer housing in the direction of the turbine space, and the cooling efficiency is noticeably improved.
  • At least one tongue-like extension is formed on the connecting piece, which extends along a flattened side of the tangential with respect to the annular gap
  • the nozzle has recesses at the point where it collides with a nozzle for an adjacent individual combustion chamber, which recesses essentially form a tight transition to corresponding recesses in the adjacent nozzle.
  • the connecting piece can be arranged in the peripheral direction
  • Individual combustion chamber can be designed to be closed, so that cooling is virtually closed over the entire circumferential area of the individual 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.
  • the individual combustion chamber is composed of an essentially cylindrically shaped inlet section downstream of the burner and a cross-fading area
  • Transition section together, wherein the nozzle at least partially surrounds the input section.
  • the input section is a thermally particularly stressed element of the individual combustion chamber, so that the possibility of quasi-closed cooling, which is given in this area due to the nozzle provided according to the invention, significantly improves the cooling of the Single combustion chamber with comparatively less cooling fluid.
  • a small amount of cooling fluid increases the economy of the gas turbine as a whole, and in those cases in which the cooling fluid is simultaneously used as fuel gas, the efficiency of the gas turbine is increased at the same time.
  • the connecting piece has a circular cross-sectional area and is arranged concentrically around the circular-cylindrical input section. This results in a uniform gap space in the circumferential direction of the inlet section, which enables 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 section of a gas turbine with a combustion chamber arrangement according to the invention
  • FIG. 2 shows a perspective view of a section of a combustion chamber arrangement according to the invention, seen from the direction of the turbine space, some of the nozzles according to the invention being provided with tongue-like extensions according to an alternative exemplary embodiment, and
  • Fig. 3 is a perspective view of a section of a combustion chamber arrangement according to the invention, seen from the direction of the burner, some of the shown nozzle according to the invention are formed with tongue-like extensions.
  • the combustion chamber arrangement 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 arrangement 1 is composed of a multiplicity of individual combustion chambers 3, which are arranged in a ring-like manner and open into a common annular gap 13.
  • the annular gap 13 in turn opens into a turbine chamber 2, in which there are schematically indicated guide vanes and rotor blades of the turbine.
  • Burners 6 are connected upstream of the individual combustion chambers 3. These serve to ignite a mixture of an oxygen-containing fuel gas and a fuel which burns further in the individual combustion chambers 3.
  • the individual combustion chambers 3 are composed of an inlet section 4 adjoining the burner 6 and a transition section 5 which transitions the inlet section 4 in the direction of the annular gap 13.
  • the burners 6 are connected to the individual combustion chambers 3 through an outer turbine housing 7.
  • 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 inlet section 4 of the individual combustion chamber 3. There is a between the nozzle 8 and the input section 4 of the individual combustion chamber 3
  • Ribs 10 with which the individual combustion chamber 3 is supported on the connection piece 8, are formed on the inlet section 4 of the individual combustion chamber 3 and are distributed along the circumference. The ribs 10 are shown in FIG.
  • Embodiment molded onto the individual combustion chamber 3 they can however also be integrally formed on the nozzle 8 and extend in the direction of the individual combustion chamber 3.
  • a recess 11 can be seen on the side of the nozzle 8, which adjoins an adjacent nozzle of an adjacent individual 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 connecting pieces 8 abut one another from a certain extent in the direction of the annular gap 13.
  • the recesses 11 are arranged in order to be able to extend the connecting piece 8 further inwards in the direction of the annular gap 13.
  • adjacent connecting pieces 8 abut one another and can be connected to one another, for example welded, for sealing.
  • the nozzles 8 arranged according to the invention form a flow channel for a cooling fluid. Due to the defined flow channel, the cooling fluid, which is guided in a quasi-closed manner in the flow channel, effectively contributes to convective cooling of the individual combustion chambers 3 in the latter
  • Nozzle 8 covered area Nozzle 8 covered area.
  • FIG. 1 two tongue-like extensions 12a and 12b lying opposite one another and running tangentially with respect to the annular gap 13 can also be seen, which are guided along the transition section 5 of the individual combustion chamber 3 while leaving a gap space.
  • These tongue-like desires 12a and 12b represent an advantageous development of the invention, but are optional. They lead to a further enlargement of the quasi closed-cooled area of the individual combustion chamber 3 and thus to a further improvement in the cooling efficiency.
  • a Basic version of a combustion chamber arrangement according to the invention can, however, only be realized with the nozzle 8 without the tongue-like extensions 12a and 12b.
  • FIGS. 2 and 3 sections from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions. In order to illustrate the different design variants with and without tongue-like extensions 12a and 12b, only a few of them are shown
  • Combustion chamber arrangement 1 creates a quasi closed, cooled area of the individual combustion chambers, in which cooling of the individual combustion chambers is possible with high efficiency.
  • the individual combustion chambers are still of simple construction, an expensive double-walled one
  • the design of the individual combustion chambers is not necessary.
  • the invention thus provides a simple means of creating 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

Beschreibungdescription
Brennkammeranordnungcombustor assembly
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 individual combustion chambers opening into a common annular gap leading into a turbine space, the individual combustion chambers being preceded by burners which are connected to the individual combustion chambers through an outer casing. 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 kreisringsegmentformigem 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.Combustion chamber arrangements of this type for gas turbines are known in the prior 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 deflected by the transition sections of the individual combustion chambers in the direction of the turbine chamber and the arrangement of guide vanes and rotor blades located therein. In this case, the hot gas streams with a circular cross-section generated in the usually circular-cylindrical inlet sections of the individual combustion chambers are converted through the transition sections into a hot gas stream with a cross-section in the form of an annular segment and finally brought together to form a circular hot gas stream. This enters the turbine space through the annular gap 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 the case of a combustion chamber arrangement shown in US Pat. No. 4,719,748, the entire single combustion chamber has a double-shell housing formed, wherein an air gap is left between the individual housing shells. A cooling fluid flows through openings in the outer housing shell into the space left between the housing shells and impacts the inner shell of the individual combustion chamber. Here, a first cooling effect is already brought about, which is referred to as brag cooling. In the further course, the cooling fluid flows through the space left between the housing shells and provides for convective cooling. This concept is also referred to as closed cooling because of the continuous double-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 designed with a simple wall. Cooling fluid flows openly past the individual combustion chambers and creates a cooling effect. Because the individual combustion chambers are designed with a simple wall, the cooling fluid flow is not directed and defined, which results in a lower overall 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,It is also known from the more recent state of the art
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. Ausgehend von diesem Stand der Technik liegt der Erfindung die A u f g a b e zugrunde, eine Brennkammeranordnung der eingangs genannten Art dahingehend weiterzuentwickeln, daß bei konstruktiv einfach gestalteten Einzelbrennkammern die Kühleffizienz erheblich gesteigert werden kann.Use mixed forms between open and closed cooling in the individual combustion chambers. In this case, the individual chambers are cooled openly over wide areas, only in an area projecting through an outer housing is a closed area to be cooled created by arranging a second wall surrounding the first wall while leaving an intermediate space. Although the individual combustion chambers used in this concept are still structurally simple, the improved cooling effect due to a very small quasi-closed cooled area is not as significant as would be desirable. Proceeding from this prior art, the invention is based on the task of further developing a combustion chamber arrangement of the type mentioned at the outset in such a way that the cooling efficiency can be increased considerably in the case of individual combustion chambers of simple design.
Zur L ö s u n g dieser Aufgabe wird vorgeschlagen, bei einer Brennkammeranordnung der eingangs genannten Art zumindest einen an einer dem Turbinenraum zugewandten Seite des Turbinenaußengehäuses angeordneten, sich radial inTo achieve this object, it is proposed that, in a combustion chamber arrangement of the type mentioned at the outset, at least one radially arranged on a side of the turbine outer housing facing the turbine space
Richtung des Turbinenraumes erstreckenden Stutzen vorzusehen, der einen Abschnitt zumindest einer Einzelbrennkammer unter Belassung eines Spaltraumes zumindest teilweise umgibt.To provide the direction of the turbine space extending stub that at least partially surrounds a portion of at least one individual combustion chamber while leaving a gap space.
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 at least one nozzle, which is arranged on the turbine outer housing and extends radially in the direction of the turbine chamber, surrounds a section of at least one individual combustion chamber located in the interior of the turbine outer housing and leaves a gap between the wall of the individual combustion chamber and the nozzle. A cooling fluid can flow into this gap space and, due to the defined flow channel, can effect a more effective convective cooling in this area. The structure of the individual combustion chamber itself remains simple, and the design of the individual combustion chamber itself is not complicated. In this way, the quasi-closed, cooled region of the individual combustion chamber is extended into the interior of the turbine outer housing in the direction of the turbine space, and 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 desIn order to enlarge the area with quasi-closed cooling even further, it is proposed according to the invention that at least one tongue-like extension is formed on the connecting piece, which extends along a flattened side of the tangential with respect to the annular gap
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.Extend transition section of the single combustion chamber leaving an intermediate space to this. Through the Arranging such a tongue, the cooling fluid used for cooling is directed even earlier into a defined space and can more effectively contribute to convective cooling of the individual combustion chamber. To create a sufficient inflow area into the intermediate space, it is advantageous if the tongue-like extension formed on the connecting piece tapers in the direction of the annular gap or the turbine space.
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 nozzles provided according to the invention as far as possible in the direction of the turbine space, it is proposed according to an advantageous development of the invention that the nozzle has recesses at the point where it collides with a nozzle for an adjacent individual combustion chamber, which recesses essentially form a tight transition to corresponding recesses in the adjacent nozzle.
Dabei kann der Stutzen gemäß einer vorteilhaften Weiterbildung der Erfindung in Umfangsrichtung derIn this case, according to an advantageous development of the invention, the connecting piece can be arranged in the peripheral direction
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.Individual combustion chamber can be designed to be closed, so that cooling is virtually closed over the entire circumferential area of the individual 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.
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 überblendendenAccording to a further development of the invention, the individual combustion chamber is composed of an essentially cylindrically shaped inlet section downstream of the burner and a cross-fading area
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.Transition section together, wherein the nozzle at least partially surrounds the input section. Because of its proximity to the burner, the input section is a thermally particularly stressed element of the individual combustion chamber, so that the possibility of quasi-closed cooling, which is given in this area due to the nozzle provided according to the invention, significantly improves the cooling of the Single combustion chamber with comparatively less cooling fluid. A small amount of cooling fluid increases the economy of the gas turbine as a whole, and in those cases in which the cooling fluid is simultaneously used as fuel gas, the efficiency of the gas turbine is increased at the same time. In the case of a circular-cylindrical design of the input section, according to a further development of the invention, it is provided that the connecting piece has a circular cross-sectional area and is arranged concentrically around the circular-cylindrical input section. This results in a uniform gap space in the circumferential direction of the inlet section, which enables 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:Further advantages and features of the invention result from the exemplary embodiments described below with reference to the accompanying drawings. The drawings show:
Fig. 1 in geschnittener Ansicht einen Abschnitt einer Gasturbine mit einer erfindungsgemäßen Brennkammeranordnung,1 shows a section of a section of a gas turbine with a combustion chamber arrangement according to the invention,
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, und2 shows a perspective view of a section of a combustion chamber arrangement according to the invention, seen from the direction of the turbine space, some of the nozzles according to the invention being provided with tongue-like extensions according to an alternative exemplary embodiment, and
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.Fig. 3 is a perspective view of a section of a combustion chamber arrangement according to the invention, seen from the direction of the burner, some of the 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 symbols.
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.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 arrangement 1 is composed of a multiplicity of individual combustion chambers 3, which are arranged in a ring-like manner and open into a common annular gap 13. The annular gap 13 in turn opens into a turbine chamber 2, in which there are schematically indicated guide vanes and rotor blades of the turbine.
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 demBurners 6 are connected upstream of the individual combustion chambers 3. These serve to ignite a mixture of an oxygen-containing fuel gas and a fuel which burns further in the individual combustion chambers 3. The individual combustion chambers 3 are composed of an inlet section 4 adjoining the burner 6 and a transition section 5 which transitions the inlet section 4 in the direction of the annular gap 13. The burners 6 are connected to the individual combustion chambers 3 through an outer turbine housing 7. Starting from that
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 einTurbine outer housing 7 in the direction of the turbine chamber 2, a nozzle 8 can be recognized, which extends concentrically around the circular cylindrical inlet section 4 of the individual combustion chamber 3. There is a between the nozzle 8 and the input section 4 of the individual combustion chamber 3
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 gezeigtenLeave gap 9, which can be flowed through by a cooling fluid. Ribs 10, with which the individual combustion chamber 3 is supported on the connection piece 8, are formed on the inlet section 4 of the individual combustion chamber 3 and are distributed along the circumference. The ribs 10 are shown in FIG
Ausführungsbeispiel an der Einzelbrennkammer 3 angeformt, sie können jedoch auch an dem Stutzen 8 angeformt sein und sich in Richtung der Einzelbrennkammer 3 erstrecken.Embodiment molded onto the individual combustion chamber 3, they can however also be integrally formed on the nozzle 8 and extend in the direction of the individual 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 adjoins an adjacent nozzle of an adjacent individual 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 connecting pieces 8 abut one another from a certain extent in the direction of the annular gap 13. At this point, the recesses 11 are arranged in order to be able to extend the connecting piece 8 further inwards in the direction of the annular gap 13. Along the edge of the recesses 11, adjacent connecting pieces 8 abut one another and can be connected to one another, for example welded, for sealing.
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 demWith their gap space 9, the nozzles 8 arranged according to the invention form a flow channel for a cooling fluid. Due to the defined flow channel, the cooling fluid, which is guided in a quasi-closed manner in the flow channel, effectively contributes to convective cooling of the individual combustion chambers 3 in the latter
Stutzen 8 überdeckten Bereich bei.Nozzle 8 covered 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 Verlangen 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 FIG. 1, two tongue-like extensions 12a and 12b lying opposite one another and running tangentially with respect to the annular gap 13 can also be seen, which are guided along the transition section 5 of the individual combustion chamber 3 while leaving a gap space. These tongue-like desires 12a and 12b represent an advantageous development of the invention, but are optional. They lead to a further enlargement of the quasi closed-cooled area of the individual combustion chamber 3 and thus to a further improvement in the cooling efficiency. A Basic version of a combustion chamber arrangement according to the invention can, however, only be realized with the nozzle 8 without the tongue-like extensions 12a and 12b.
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 dieIn FIGS. 2 and 3, sections from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions. In order to illustrate the different design variants with and without tongue-like extensions 12a and 12b, only a few of them are shown
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 derIndividual combustion chamber 3, at least in the inlet section 4 surrounding nozzle 8 with the tongue-like extension 12a or 12b shown. In FIG. 2, the course of the flow 14 of a coolant fluid from the openly cooled area in the direction of the gap spaces below the tongue-like extensions 12a and subsequently below the connection piece 8 is also shown with the aid of arrows. It can also be seen that the tongue-like extensions 12a or 12b extend in the direction of the exit from the transition section 5 of the transition into the gap space
Einzelbrennkammern 3 hin verjüngen. Hierdurch wird eine ausreichend große Eintrittsfläche für den Kühlfluidstrom gewährleistet .Taper individual combustion chambers 3. This ensures a sufficiently large entry area for the cooling fluid flow.
Zu erkennen ist, daß mit der erfindungsgemäßenIt can be seen that with the invention
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 doppelwandigeCombustion chamber arrangement 1 creates a quasi closed, cooled area of the individual combustion chambers, in which cooling of the individual combustion chambers is possible with high efficiency. The individual combustion chambers are still of simple construction, an expensive double-walled one
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. The design of the individual combustion chambers is not necessary. The invention thus provides a simple means of creating a simple combustion chamber arrangement with the possibility of highly efficient cooling.

Claims

Patentansprüche claims
1. Brennkammeranordnung für eine Gasturbine mit einer Vielzahl von in einem gemeinsamen, in einen Turbinenraum (2) überleitenden Ringspalt (13) mündenden Einzelbrennkammern (3) , wobei den Einzelbrennkammern (3) Brenner (6) vorgeschaltet sind, die mit den Einzelbrennkammern (3) durch ein Turbinenaußengehäuse (7) hindurch verbunden sind, wobei an einer dem Turbinenraum (2) zugewandten Seite des Turbinenaußengehäuses (7) ein sich radial in Richtung des1. Combustion chamber arrangement for a gas turbine with a plurality of individual combustion chambers (3) opening into a common annular gap (13) which leads into a turbine space (2), the individual combustion chambers (3) being preceded by burners (6) which are connected to the individual combustion chambers (3 ) are connected through a turbine outer casing (7), with a radial direction in the direction of the. on a side of the turbine outer casing (7) facing the turbine space (2)
Turbinenraumes (2) erstreckender Stutzen (8) angeordnet ist, der einen Abschnitt zumindest einer der EinzelbrennkammernTurbine chamber (2) extending stub (8) is arranged, a portion of at least one of the individual combustion chambers
(3) unter Belassung eines Spaltraumes (9) zumindest teilweise umgibt , g e k e n n z e i c h n e t d u r c h, eine an dem Stutzen (8) ausgebildete, zungenartige Verlängerung (12a, 12b) , welche einer bezüglich des Ringspaltes tangentiale, abgeflachte Seite des Übergangsabschnittes (5) unter Belassung eines Spaltraumes überragt.(3) at least partially surrounds leaving a gap space (9), characterized by a tongue-like extension (12a, 12b) formed on the connecting piece (8), which has a flattened side of the transition section (5) which is tangential with respect to the annular gap while leaving a Gap tower dominated.
2. Brennkammeranordnung nach Anspruch 1 , d a d u r c h g e k e n n z e i c h n e t, daß der mindestens eine Stutzen (8) in Umfangsrichtung der Einzelbrennkammer (3) geschlossen ausgebildet ist.2. Combustion chamber arrangement according to claim 1, so that the at least one nozzle (8) is designed to be closed in the circumferential direction of the individual combustion chamber (3).
3. Brennkammeranordnung nach einem der Ansprüche 1 oder 2 , d a d u r c h g e k e n n z e i c h n e t, daß die Einzelbrennkammer (3) aus einem im wesentlichen zylindrisch geformten, dem Brenner (6) nachgeschalteten Eingangsabschnitt3. Combustion chamber arrangement according to one of claims 1 or 2, d a d u r c h g e k e n n z e i c h n e t that the individual combustion chamber (3) from an essentially cylindrical shaped, the burner (6) downstream input section
(4) und einem in einen kreisringsektorförmigen Querschnitt überblendenden Übergangsabschnitt (5) besteht, wobei der Stutzen (8) zumindest den Eingangsabschnitt (4) mindestens teilweise umgibt.(4) and a transition section (5) which cross-fades into an annular sector cross-section, the connecting piece (8) at least partially surrounding the input section (4).
4. Brennkammeranordnung nach Anspruch 3 , d a d u r c h g e k e n n z e i c h n e t, daß der Eingangsabschnitt (4) kreiszylindrisch ausgebildet ist und daß der Stutzen (8) eine kreisförmige Querschnittsfläche aufweist und konzentrisch um den Eingangsabschnitt (4) herum angeordnet ist .4. Combustion chamber arrangement according to claim 3, characterized in that the Input section (4) is circular cylindrical and that the connector (8) has a circular cross-sectional area and is arranged concentrically around the input section (4).
5. Brennkammeranordnung nach Anspruch 1 , d a d u r c h g e k e n n z e i c h n e t, daß die zungenartige Verlängerung (12a, 12b) in Richtung des Ringspalts (13) verjüngt ausgebildet ist.5. Combustion chamber arrangement according to claim 1, so that the tongue-like extension (12a, 12b) is tapered in the direction of the annular gap (13).
6. Brennkammeranordnung nach einem der Ansprüche 1 bis 5, d a d u r c h g e k e n n z e i c h n e t, daß die Stutzen6. combustion chamber arrangement according to one of claims 1 to 5, d a d u r c h g e k e n n z e i c h n e t that the nozzle
(8) in dem Bereich, in dem sie mit um benachbarte Einzelbrennkammern (3) angeordnete Stutzen (8) zusammentreffen, seitliche Ausnehmungen (11) aufweisen, entlang derer die benachbarten Stutzen (8) im wesentlichen dichtend aneinander anliegen.(8) in the area in which they meet with nozzles (8) arranged around adjacent individual combustion chambers (3), have lateral recesses (11) along which the adjacent nozzles (8) lie essentially sealingly against one another.
7. Brennkammeranordnung nach Anspruch 6 , d a d u r c h g e k e n n z e i c h n e t, daß die benachbarten Stutzen entlang der Ränder der Ausnehmungen (11) miteinander verbunden sind.7. combustion chamber arrangement according to claim 6, d a d u r c h g e k e n n z e i c h n e t that the adjacent nozzle along the edges of the recesses (11) are interconnected.
8. Gasturbine, g e k e n n z e i c h n e t d u r c h eine Brennkammeranordnung (1) nach einem der Ansprüche 1 bis 7. 8. Gas turbine, g e k e n n z e i c h n e t d u r c h 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)

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

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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7155800B2 (en) 2005-02-24 2007-01-02 General Electric Company Automated seal strip assembly method and apparatus for rotary machines
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
EP2211023A1 (en) 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Guide vane system for a turbomachine with segmented guide vane carrier
US8201412B2 (en) * 2010-09-13 2012-06-19 General Electric Company Apparatus and method for cooling a combustor
DE102011007562A1 (en) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Combustor housing and thus equipped gas turbine
US8650852B2 (en) * 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
US3840332A (en) * 1973-03-05 1974-10-08 Stone Platt Crawley Ltd Combustion chambers
GB1492049A (en) * 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPS59229114A (en) * 1983-06-08 1984-12-22 Hitachi Ltd Combustor for gas turbine
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
US4794753A (en) * 1987-01-06 1989-01-03 General Electric Company Pressurized air support for catalytic reactor
GB9220937D0 (en) * 1992-10-06 1992-11-18 Rolls Royce Plc Gas turbine engine combustor
US5323600A (en) * 1993-08-03 1994-06-28 General Electric Company Liner stop assembly for a combustor
FR2710968B1 (en) * 1993-10-06 1995-11-03 Snecma Double wall combustion chamber.
US6182451B1 (en) * 1994-09-14 2001-02-06 Alliedsignal Inc. Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor
US5737913A (en) * 1996-10-18 1998-04-14 The United States Of America As Represented By The Secretary Of The Air Force Self-aligning quick release engine case assembly
JP3110338B2 (en) * 1997-02-12 2000-11-20 東北電力株式会社 Combustor cooling structure with steam
GB2328011A (en) * 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
DE19801626B4 (en) * 1998-01-17 2010-08-12 Robert Bosch Gmbh Diagnosis of a NOx storage catalytic converter in the operation of internal combustion engines
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
US6354071B2 (en) * 1998-09-25 2002-03-12 General Electric Company Measurement method for detecting and quantifying combustor dynamic pressures
US6216442B1 (en) * 1999-10-05 2001-04-17 General Electric Co. Supports for connecting a flow sleeve and a liner in a gas turbine combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO03021149A1 *

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JP2005502020A (en) 2005-01-20
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