EP2487417A1 - Combustion chamber casing - Google Patents

Combustion chamber casing Download PDF

Info

Publication number
EP2487417A1
EP2487417A1 EP11153769A EP11153769A EP2487417A1 EP 2487417 A1 EP2487417 A1 EP 2487417A1 EP 11153769 A EP11153769 A EP 11153769A EP 11153769 A EP11153769 A EP 11153769A EP 2487417 A1 EP2487417 A1 EP 2487417A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shell
wear
wear ring
outer shell
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
EP11153769A
Other languages
German (de)
French (fr)
Other versions
EP2487417B1 (en
Inventor
Andreas Dr. Böttcher
Christopher Grandt
Thomas Kunadt
Wilhelm Scheidtmann
Holger Streb
Daniel Vogtmann
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to HUE11153769A priority Critical patent/HUE027667T2/en
Priority to EP11153769.2A priority patent/EP2487417B1/en
Priority to RU2012104494/06A priority patent/RU2583327C2/en
Priority to CN201210026875.XA priority patent/CN102635875B/en
Publication of EP2487417A1 publication Critical patent/EP2487417A1/en
Application granted granted Critical
Publication of EP2487417B1 publication Critical patent/EP2487417B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F23R3/002—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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a combustion chamber housing, which is formed by a combustion chamber outer shell with a shell interior and a combustion chamber inner shell with a shell interior.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
  • Solid-Fuel Combustion (AREA)

Abstract

The combustion chamber housing has a shell inner side and a combustion chamber inner shell (30) with an inner shell. The combustion chamber outer shell (20) and combustion chamber inner shell have an open, continuous, circumferential recess (27,37) at the inner side of the shell. A two-piece wear plate is provided in the recesses.

Description

Die Erfindung betrifft ein Brennkammergehäuse, welches durch eine Brennkammeraußenschale mit einem Schaleninneren und eine Brennkammerinnenschale mit einem Schaleninneren gebildet ist.The invention relates to a combustion chamber housing, which is formed by a combustion chamber outer shell with a shell interior and a combustion chamber inner shell with a shell interior.

Eine Gasturbine weist einen um eine Rotationsachse drehgelagerten Rotor mit einer Welle auf. Entlang dem Rotor folgen aufeinander ein Ansauggehäuse, ein Verdichter, eine Brennkammer (beispielsweise eine Ringbrennkammer) mit einem Brennkammergehäuse zum Führen von Heißgas und mit mehreren koaxial angeordneten Brennern, eine Turbine und ein Abgasgehäuse.A gas turbine has a rotor rotatably mounted about a rotation axis with a shaft. Along the rotor follow one another an intake housing, a compressor, a combustion chamber (for example an annular combustion chamber) with a combustion chamber housing for guiding hot gas and with a plurality of coaxially arranged burners, a turbine and an exhaust housing.

Das Brennkammergehäuse wird durch eine ringförmige Brennkammeraußenschale und eine Brennkammerinnenschale gebildet. Dabei werden die Brennkammeraußenschale und eine Brennkammerinnenschale stirnseitig, das heißt stromaufwärts, bislang über ein Andrückblech mit zwei L-Ringen verbunden. Diese L-Ringe neigen jedoch im Betrieb zu starker Verzunderung. Auch findet ein Verschleiß zwischen den L-Ringen und der Brennkammerau-βenschale bzw. der Brennkammerinnenschale statt. Das Andrückblech zeichnet sich ebenfalls durch hohe Verschleißanfälligkeit und damit kurze Lebensdauer aus. Aufgrund des hohen Verschleißes muss daher das Dichtblech mit den L-Ringen am Brennkammergehäuse häufig getauscht werden. Die Montage dieser Komponenten am Brennkammergehäuse ist jedoch sehr langwierig und auch sehr schwer.The combustion chamber housing is formed by an annular combustion chamber outer shell and a combustion chamber inner shell. In this case, the combustion chamber outer shell and a combustion chamber inner shell at the front, that is upstream, previously connected via a pressure plate with two L-rings. However, these L-rings tend in operation to strong scaling. Also, wear between the L-rings and the Brennkammerau-βenschale or the combustion chamber inner shell takes place. The pressure plate is also characterized by high susceptibility to wear and thus short life. Due to the high wear, therefore, the sealing plate with the L-rings on the combustion chamber housing must be frequently replaced. The assembly of these components on the combustion chamber housing is very tedious and very difficult.

Aufgabe der Erfindung ist es, ein Brennkammergehäuse anzugeben, welches die oben beschriebenen Nachteile vermeidet.The object of the invention is to provide a combustion chamber housing which avoids the disadvantages described above.

Erfindungsgemäß wird diese Aufgabe gelöst durch die Angabe eines Brennkammergehäuses gemäß Anspruch 1. Vorteilhafte Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen definiert. Durch ein Brennkammergehäuse, welches durch eine Brennkammeraußenschale mit einem Schaleninneren und eineAccording to the invention this object is achieved by the specification of a combustion chamber housing according to claim 1. Advantageous developments of the invention are defined in the dependent claims. Through a combustion chamber housing, which by a combustion chamber outer shell with a shell interior and a

Brennkammerinnenschale mit einem Schaleninneren gebildet ist, wobei die Brennkammeraußenschale und die Brennkammerinnenschale jeweils eine zu einer Stirnseite offene, durchgängige, umlaufende Aussparung zu dem Schaleninneren aufweisen, wobei in diesen Aussparungen eine zweiteilige Verschleißleiste vorgesehen ist, wobei die Verschleißleiste mit der Brennkammeraußenschale als auch mit der Brennkammerinnenschale lösbar verbunden ist, wird folgendes erreicht:Combustor inner shell is formed with a shell interior, the combustion chamber outer shell and the inner combustion chamber each having an open, continuous, circumferential recess to the shell interior, wherein in these recesses, a two-part wear strip is provided, wherein the wear strip with the combustion chamber outer shell and the combustion chamber inner shell is detachably connected, the following is achieved:

Durch die Anbringung der Verschleißleiste in der zu einer Stirnseite offenen, durchgängigen, umlaufenden Aussparung und die lösbare Verbindung dieser Verschleißleiste ist diese bei Verschleißerscheinungen einfach abzumontieren. Ebenso einfach kann eine neue Verschleißleiste hinmontiert werden. Die Verschleißleiste kann bei der Revision daher einfach ausgetauscht werden. Der Austausch der Verschleißleiste ist im Hinblick auf die Montagekosten wesentlich kostengünstiger als ein Austausch der L-Ringe im Stand der Technik. Zudem kann eine solche Verschleißleiste sehr dick ausgeführt werden, was die Lebensdauer einer solchen Verschleißleiste wesentlich erhöht. Zudem findet der Verschleiß nur noch an der austauschbaren Verschleißleiste statt, und nicht mehr wie im Stand der Technik zwischen den L-Ringen und der Brennkammerinnenschale bzw. Brennkammeraußenschale.By attaching the wear strip in the open to one end, continuous, circumferential recess and the detachable connection of this wear strip this is easy to dismantle in case of wear. Just as easily, a new wear strip can be mounted. The wear strip can therefore be easily replaced during the revision. The replacement of the wear strip is much cheaper in terms of assembly costs than a replacement of the L-rings in the prior art. In addition, such a wear strip can be made very thick, which significantly increases the life of such a wear strip. In addition, the wear takes place only on the replaceable wear strip, and no longer as in the prior art between the L-rings and the inner combustion chamber shell or combustion chamber outer shell.

Vorteilhafterweise besteht die Verschleißleiste aus einem ersten Verschleißring und einem zweiten Verschleißring, wobei der erste Verschleißring einen Vorsprung aufweist, und der zweite Verschleißring eine zum Vorsprung korrespondierende Nut aufweist, so dass der Vorsprung in die Nut einbringbar ist, und der Vorsprung dadurch in der Nut fixierbar ist. Dadurch können Brennkammerinnenschale und Brennkammeraußenschale leicht in der Montage positioniert und verbunden werden, da sie sich durch den Vorsprung und die Nut einfach zueinander zentrieren lassen (selbstzentrierende Verbindung).Advantageously, the wear strip consists of a first wear ring and a second wear ring, wherein the first wear ring has a projection, and the second wear ring has a groove corresponding to the projection, so that the projection can be introduced into the groove, and the projection thereby fixable in the groove is. As a result, combustion chamber inner shell and combustion chamber outer shell can be easily positioned in the assembly and connected because they can be centered by the projection and the groove easy to each other (self-centering connection).

Vorteilhafterweise ist zwischen dem Vorsprung und der zum Vorsprung korrespondierenden Nut eine Dehnspalte vorgesehen. Dadurch können temperaturbedingte Ausdehnungen des Materials besser kompensiert werden.Advantageously, a Dehnspalte is provided between the projection and the groove corresponding to the projection. As a result, temperature-induced expansions of the material can be better compensated.

In vorteilhafter Ausgestaltung ist der erste Verschleißring in der zur Brennkammeraußenschale gehörenden Aussparung vorgesehen, wobei der erste Verschleißring mit der Brennkammeraußenschale verschraubt ist und der zweite Verschleißring in der zur Brennkammerinnenschale gehörenden Aussparung, wobei der zweite Verschleißring mit der Brennkammerinnenschale verschraubt. Alternativ ist der erste Verschleißring in der zur Brennkammerinnenschale gehörenden Aussparung vorgesehen, wobei der erste Verschleißring mit der Brennkammerinnenschale verschraubt ist und der zweite Verschleißring in der zur Brennkammeraußenschale gehörenden Aussparung, wobei der zweite Verschleißring mit der Brennkammeraußenschale verschraubt ist. Eine solche Schraubverbindung lässt sich leicht lösen und kann zudem temperaturbeständig ausgebildet sein. Auch andere lösbare Verbindungen sind jedoch vorstellbar.In an advantageous embodiment, the first wear ring is provided in the recess belonging to the combustion chamber outer shell, wherein the first wear ring is bolted to the combustion chamber outer shell and the second wear ring in the recess belonging to the combustion chamber inner shell, wherein the second wear ring bolted to the combustion chamber inner shell. Alternatively, the first wear ring is provided in the recess belonging to the combustion chamber inner shell, wherein the first wear ring is screwed to the combustion chamber inner shell and the second wear ring in the recess belonging to the combustion chamber outer shell, wherein the second wear ring is screwed to the combustion chamber outer shell. Such a screw connection can be easily solved and can also be formed temperature resistant. However, other releasable connections are conceivable.

Zweckmäßiger Weise umfasst eine Gasturbine ein Brennkammergehäuse gemäß der Erfindung.Conveniently, a gas turbine comprises a combustion chamber housing according to the invention.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren 1 bis 3.

Figur 1
zeigt einen Halbschnitt durch eine Gasturbinenanlage.
Figur 2
zeigt ausschnittsweise einen Querschnitt eines erfindungsgemäßen Brennkammergehäuses.
Figur 3
zeigt ausschnittsweise die Stirnseite eines erfindungsgemäßen Brennkammergehäuses.
Further features, characteristics and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying FIGS. 1 to 3 ,
FIG. 1
shows a half section through a gas turbine plant.
FIG. 2
shows a detail of a cross section of a combustion chamber housing according to the invention.
FIG. 3
shows a detail of the front side of a combustion chamber housing according to the invention.

Eine Gasturbinenanlage 1 gemäß Figur 1 weist einen Verdichter 2 für Verbrennungsluft, eine Brennkammer 4 sowie eine Turbine 6 zum Antrieb des Verdichters 2 und eines nicht dargestellten Generators auf. Die Brennkammer 4 ist mit einer Anzahl von Brennern 10 zur Verbrennung eines flüssigen oder gasförmigen Brennstoffs bestückt. Sie weist zudem eine Brennkammeraußenschale 20 und eine Brennkammerinnenschale 30, auch Nabe genannt, auf.A gas turbine plant 1 according to FIG. 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator, not shown. The combustion chamber 4 is provided with a number of Burners 10 equipped for the combustion of a liquid or gaseous fuel. It also has a combustion chamber outer shell 20 and a combustion chamber inner shell 30, also called hub on.

Die Turbine 6 weist eine Anzahl rotierbaren Laufschaufeln 12 auf. Weiterhin umfasst die Turbine 6 eine Anzahl von feststehenden Leitschaufeln 14. Die Laufschaufeln 12 dienen dabei zum Antrieb der Turbinenwelle 8 durch Impulsübertrag vom die Turbine 6 durchströmenden Arbeitsmedium M. Die Leitschaufeln 14 dienen hingegen zur Strömungsführung des Arbeitsmediums M zwischen jeweils zwei in Strömungsrichtung des Arbeitsmediums M gesehen aufeinander folgenden Laufschaufelreihen oder Laufschaufelkränzen. Die Erfindung betrifft den mit 11 bezeichneten Bereich und wird in den Figuren 2 und 3 beschrieben.The turbine 6 has a number of rotatable blades 12. The rotor blades 6 serve to drive the turbine shaft 8 by momentum transfer from the turbine medium 6 flowing through the working medium M. The guide vanes 14, however, serve to guide the flow of the working medium M between two each in the flow direction of the working medium M. seen consecutive blade rows or blade rings. The invention relates to the area designated 11 and is in the FIGS. 2 and 3 described.

Fig. 2 zeigt ausschnittsweise eine Brennkammeraußenschale 20 mit einem Schaleninneren und eine Brennkammerinnenschale 30 mit einem Schaleninneren. Die Brennkammeraußenschale 20 als auch die Brennkammerinnenschale 30 weisen zu einer Stirnseite 5 offene, durchgängige, umlaufende Aussparungen 27,37 auf, welche zu dem Schaleninneren zeigen. In dieser Aussparung 27,37 ist eine Verschleißleiste vorgesehen. Die Verschleißleiste besteht dabei aus einem ersten Verschleißring 25 und einem zweiten Verschleißring 35. Der erste Verschleißring 25 weist einen Vorsprung 26 auf, während der zweite Verschleißring 35 eine zum Vorsprung 26 korrespondierende Nut 36 aufweist. Der Vorsprung 26 ist in die Nut 36 einbringbar. Beim Montieren der Brennkammeraußenschale 20 zu der Brennkammerinnenschale 30, rutscht der Vorsprung 26 in die Nut 36 ein, so dass eine Zentrierung der Brennkammeraußenschale 20 zu der Brennkammerinnenschale 30 stattfindet. Diese vereinfachte Zentrierung erspart viel Montagezeit. Zudem fixiert der Vorsprung 26 mit der Nut 36 im Betrieb die Brennkammeraußenschale 20 zu der Brennkammerinnenschale 30. Die Verschleißleiste 25 ist mit Schrauben 40 in der zur Stirnseite 5 offenen Aussparung 27 der Brennkammeraußenschale 20 angebracht. Die Verschleißleiste 35 ist ebenfalls mit Schrauben 40 in der zur Stirnseite 5 offenen Aussparung 37 der Brennkammerinnenschale 30 angebracht. Anstatt Schrauben 40 kann auch eine beliebige andere lösbare Verbindung herangezogen werden. Wird nun ein Verschleiß bei dem Verschleißring 25 bzw. 35 oder den beiden Verschleißringen 35 und 25 festgestellt, so können die Schrauben 40 gelöst und die Verschleißringe 25,35 ausgetauscht werden. Durch die Anbringung der Verschleißringen 35 und 25 an den zur Stirnseite 5 offenen, durchgängigen, umlaufenden Aussparungen 27 und 37 und die lösbare Schraubverbindung können die Verschleißringe 25 und 35 bei Verschleißbefund einfach abmontiert werden. Auch können die Verschleißringe 25 und 35 in ihrer Dicke und Länge sehr viel Material aufweisen, so dass die Verschleißringe 25 und 35 eine hohe Lebensdauer aufweisen. Der Verschleiß findet nun zudem lediglich bei den beiden Verschleißringen 25 und 35 statt und nicht mehr, wie im Stand der Technik, zwischen den L-Ringen und der Brennkammeraußenschale 20 bzw. der Brennkammerinnenschale 30. Dies erhöht auch die Lebensdauer der Brennkammeraußenschale 20 bzw. der Brennkammerinnenschale 30. Zwischen den Vorsprung 26 und der Nut 36 kann eine Dehnspalte 41 vorhanden sein, welche thermische Ausdehnungen im Betrieb kompensiert. Fig. 2 1 shows a detail of a combustion chamber outer shell 20 with a shell interior and a combustion chamber inner shell 30 with a shell interior. The combustion chamber outer shell 20 and the combustion chamber inner shell 30 have open to one end face 5, continuous, circumferential recesses 27,37, which point to the shell interior. In this recess 27,37 a wear strip is provided. The wear strip consists of a first wear ring 25 and a second wear ring 35. The first wear ring 25 has a projection 26, while the second wear ring 35 has a groove 26 corresponding to the projection 36. The projection 26 can be introduced into the groove 36. When mounting the combustion chamber outer shell 20 to the combustion chamber inner shell 30, the projection 26 slips into the groove 36, so that a centering of the combustion chamber outer shell 20 takes place to the combustion chamber inner shell 30. This simplified centering saves a lot of assembly time. In addition, the protrusion 26 with the groove 36 in operation fixes the combustion chamber outer shell 20 to the combustion chamber inner shell 30. The wear strip 25 is attached with screws 40 in the recess 27 of the combustion chamber outer shell 20 that is open towards the end side 5. The wear strip 35 is also with screws 40 in the for End face 5 open recess 37 of the combustion chamber inner shell 30 is attached. Instead of screws 40 can also be used any other releasable connection. If wear is now detected in the wear ring 25 or 35 or the two wear rings 35 and 25, the screws 40 can be loosened and the wear rings 25, 35 exchanged. By attaching the wear rings 35 and 25 on the open to the front side 5, continuous, circumferential recesses 27 and 37 and the detachable screw connection, the wear rings 25 and 35 can be easily removed in the event of wear. Also, the wear rings 25 and 35 can have a large amount of material in their thickness and length, so that the wear rings 25 and 35 have a long service life. The wear now also takes place only in the two wear rings 25 and 35 and no longer, as in the prior art, between the L-rings and the combustion chamber outer shell 20 and the combustion chamber inner shell 30. This also increases the life of the combustion chamber outer shell 20 and Combustor inner shell 30. Between the projection 26 and the groove 36 may be an expansion column 41, which compensates for thermal expansion during operation.

Figur 3 zeigt ausschnittsweise die Stirnseite 5 eines erfindungsgemäßen Brennkammergehäuses. Schrauben 40 sind dabei äquidistant über den Verschleißring 25 verteilt, ebenso wie Schrauben 40 äquidistant über den Verschleißring 35 verteilt sind. Dabei können die Schrauben 40 des ersten Verschleißringes 25 versetzt zu den Schrauben 40 des zweiten Verschleißringes 35 angeordnet sein. Anstatt Schrauben 40 können auch beliebig andere, lösbare Verbindungen herangezogen werden. FIG. 3 shows a detail of the end face 5 of a combustion chamber housing according to the invention. Screws 40 are distributed equidistantly over the wear ring 25, as well as screws 40 are equidistantly distributed over the wear ring 35. In this case, the screws 40 of the first wear ring 25 can be arranged offset to the screws 40 of the second wear ring 35. Instead of screws 40, any other releasable connections can be used.

Claims (6)

Brennkammergehäuse, welches durch eine Brennkammeraußenschale (20) mit einem Schaleninneren und eine Brennkammerinnenschale (30) mit einem Schaleninneren gebildet ist, dadurch gekennzeichnet, dass die Brennkammeraußenschale (20) und die Brennkammerinnenschale (30) jeweils eine zu einer Stirnseite (5) offene, durchgängige, umlaufende Aussparung (27,37) zu dem Schaleninneren aufweisen, wobei in diesen Aussparungen (27,37) eine zweiteilige Verschleißleiste vorgesehen ist, wobei die Verschleißleiste mit der Brennkammeraußenschale (20) als auch mit der Brennkammerinnenschale (30) lösbar verbunden ist.Combustion chamber housing, which is formed by a combustion chamber outer shell (20) with a shell interior and a combustion chamber inner shell (30) with a shell interior, characterized in that the combustion chamber outer shell (20) and the combustion chamber inner shell (30) in each case one to a front side (5) open, continuous , circumferential recess (27,37) to the shell interior, wherein in these recesses (27,37) is provided a two-part wear strip, wherein the wear strip with the combustion chamber outer shell (20) and with the combustion chamber inner shell (30) is detachably connected. Brennkammergehäuse nach Anspruch 1,
dadurch gekennzeichnet, dass die Verschleißleiste aus einem ersten Verschleißring (25) und einem zweiten Verschleißring (35) besteht, wobei der erste Verschleißring (25) einen Vorsprung (26) aufweist und der zweite Verschleißring (35) eine zum Vorsprung (26) korrespondierende Nut (36) aufweist, so dass der Vorsprung (26) in die Nut (36) einbringbar ist, und der Vorsprung (26) dadurch in der Nut (36) fixierbar ist.Combustion chamber housing according to claim 1,
characterized in that the wear strip of a first wear ring (25) and a second wear ring (35), wherein the first wear ring (25) has a projection (26) and the second wear ring (35) has a projection (26) corresponding groove (36), so that the projection (26) in the groove (36) can be introduced, and the projection (26) is thereby fixable in the groove (36). Brennkammergehäuse nach Anspruch 2,
dadurch gekennzeichnet, dass zwischen Vorsprung (26) und der zum Vorsprung (26) korrespondierenden Nut (36) eine Dehnspalte (41) vorgesehen ist.Combustion chamber housing according to claim 2,
characterized in that an expansion gap (41) is provided between the projection (26) and the projection (26) corresponding groove (36). Brennkammergehäuse nach Anspruch 2 oder 3,
dadurch gekennzeichnet, dass der erste Verschleißring (25) in der zur Brennkammeraußenschale (20) gehörenden Aussparung (27) vorgesehen ist und wobei der erste Verschleißring (25) mit der Brennkammeraußenschale (20) verschraubt ist und der zweite Verschleißring (35) in der zur Brennkammerinnenschale (30) gehörenden Aussparung vorgesehen ist und wobei der zweite Verschleißring (35) mit der Brennkammerinnenschale (30) verschraubt ist.Combustion chamber housing according to claim 2 or 3,
characterized in that the first wear ring (25) is provided in the recess (27) associated with the combustion chamber outer shell (20) and wherein the first wear ring (25) is bolted to the combustion chamber outer shell (20) and the second wear ring (35) is in the Combustion chamber inner shell (30) belonging recess is provided and wherein the second wear ring (35) with the combustion chamber inner shell (30) is screwed. Brennkammergehäuse nach Anspruch 2 oder 3,
dadurch gekennzeichnet, dass der erste Verschleißring (25) in der zur Brennkammerinnenschale (30) gehörenden Aussparung (37) vorgesehen ist und wobei der erste Verschleißring (25) mit der Brennkammerinnenschale (30) verschraubt ist und der zweite Verschleißring (35) in der zur Brennkammeraußenschale (20) gehörenden Aussparung (27) vorgesehen ist und wobei der zweite Verschleißring (35) mit der Brennkammeraußenschale (20) verschraubt ist.Combustion chamber housing according to claim 2 or 3,
characterized in that the first wear ring (25) is provided in the recess (37) belonging to the combustion chamber inner shell (30) and wherein the first wear ring (25) is screwed to the combustion chamber inner shell (30) and the second wear ring (35) is in the A combustion chamber outer shell (20) belonging recess (27) is provided and wherein the second wear ring (35) with the combustion chamber outer shell (20) is screwed. Gasturbine mit einem Brennkammergehäuse nach einem der vorhergehenden Ansprüche.Gas turbine with a combustion chamber housing according to one of the preceding claims.
EP11153769.2A 2011-02-09 2011-02-09 Combustion chamber casing Active EP2487417B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
HUE11153769A HUE027667T2 (en) 2011-02-09 2011-02-09 Combustion chamber casing
EP11153769.2A EP2487417B1 (en) 2011-02-09 2011-02-09 Combustion chamber casing
RU2012104494/06A RU2583327C2 (en) 2011-02-09 2012-02-08 Combustion chamber housing
CN201210026875.XA CN102635875B (en) 2011-02-09 2012-02-08 Combustion box

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11153769.2A EP2487417B1 (en) 2011-02-09 2011-02-09 Combustion chamber casing

Publications (2)

Publication Number Publication Date
EP2487417A1 true EP2487417A1 (en) 2012-08-15
EP2487417B1 EP2487417B1 (en) 2015-07-15

Family

ID=44146266

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11153769.2A Active EP2487417B1 (en) 2011-02-09 2011-02-09 Combustion chamber casing

Country Status (4)

Country Link
EP (1) EP2487417B1 (en)
CN (1) CN102635875B (en)
HU (1) HUE027667T2 (en)
RU (1) RU2583327C2 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312865A1 (en) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Gas turbine annular combustion chamber
EP1903283A1 (en) * 2006-09-22 2008-03-26 Snecma Annular combustion chamber of a turbomachine
US20100058763A1 (en) * 2008-09-11 2010-03-11 Rubio Mark F Segmented annular combustor
US20100139283A1 (en) * 2008-12-09 2010-06-10 Stephen Phillips Combustor liner with integrated anti-rotation and removal feature

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB892890A (en) * 1958-11-25 1962-04-04 Joseph Thompson Purvis Annular combustion chamber reinforcing means
ES2117402T3 (en) * 1994-01-24 1998-08-01 Siemens Ag PROCEDURE FOR THE COMBUSTION OF A COMBUSTIBLE IN COMPRESSED AIR.
EP1473517A1 (en) * 2003-04-30 2004-11-03 Siemens Aktiengesellschaft Combustion chamber
EP1521018A1 (en) * 2003-10-02 2005-04-06 ALSTOM Technology Ltd High temperature seal
US20070119052A1 (en) * 2005-11-28 2007-05-31 General Electric Company Combustor dome repair method
FR2897923B1 (en) * 2006-02-27 2008-06-06 Snecma Sa ANNULAR COMBUSTION CHAMBER WITH REMOVABLE BACKGROUND
RU2315911C1 (en) * 2006-06-07 2008-01-27 Михаил Иванович Весенгириев Annular combustion chamber of gas-turbine engine
US7909300B2 (en) * 2007-10-18 2011-03-22 General Electric Company Combustor bracket assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312865A1 (en) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Gas turbine annular combustion chamber
EP1903283A1 (en) * 2006-09-22 2008-03-26 Snecma Annular combustion chamber of a turbomachine
US20100058763A1 (en) * 2008-09-11 2010-03-11 Rubio Mark F Segmented annular combustor
US20100139283A1 (en) * 2008-12-09 2010-06-10 Stephen Phillips Combustor liner with integrated anti-rotation and removal feature

Also Published As

Publication number Publication date
RU2012104494A (en) 2013-08-20
RU2583327C2 (en) 2016-05-10
CN102635875B (en) 2016-05-04
EP2487417B1 (en) 2015-07-15
HUE027667T2 (en) 2016-10-28
CN102635875A (en) 2012-08-15

Similar Documents

Publication Publication Date Title
DE2439339C2 (en) Gas turbine
DE3140693C1 (en) Housing construction for a gas turbine engine
DE10318852A1 (en) Main gas duct inner seal of a high pressure turbine
DE102007031712A1 (en) Device and method for clamping bladed rotor disks of a jet engine
DE1601679A1 (en) Stator arrangement for turbines
EP2211023A1 (en) Guide vane system for a turbomachine with segmented guide vane carrier
EP1816401B1 (en) Turbomachine
EP2799776A1 (en) Burner seal for gas turbine combustion chamber head and heat shield
DE102008010294A1 (en) Gas turbine combustor with ceramic flame tube
DE1476733B1 (en) Bearing for the inlet guide vane ring of the first turbine stage of a gas turbine engine
DE1185865B (en) Axial turbine with inlet guide vanes that can be removed axially towards the front
DE2920193A1 (en) COOLING AIR SUPPLY ARRANGEMENT FOR A GAS TURBINE ENGINE
EP1960636B1 (en) Turbomachine
EP2487417B1 (en) Combustion chamber casing
EP2526263A2 (en) Housing system for an axial turbomachine
EP2378103B1 (en) Aircraft gas turbine drive
EP3921577B1 (en) Tubular combustion chamber system and gas turbine unit having a tubular combustion chamber system of this type
WO2013144040A1 (en) Carrier ring
DE2218500A1 (en) MULTIPLE AXIAL TURBINE FOR HIGH STEAM PRESSURE AND TEMPERATURES
EP3921576B1 (en) Resonator, method for producing such a resonator, and combustor arrangement equipped with such a resonator
EP2362142A1 (en) Burner assembly
DE102013210171A1 (en) Structural assembly for a turbomachine
EP2402659A1 (en) Combustion chamber external jacket
DE768036C (en) Attachment of the end bearing of a turbine shaft to the turbine housing, especially for aircraft combustion turbines
DE1278183B (en) Pressurized gas starting device for a gas turbine jet engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

17P Request for examination filed

Effective date: 20130206

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/00 20060101AFI20150112BHEP

Ipc: F23R 3/50 20060101ALI20150112BHEP

Ipc: F23R 3/60 20060101ALI20150112BHEP

INTG Intention to grant announced

Effective date: 20150210

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 737003

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502011007319

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20150715

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151016

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151116

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502011007319

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

26N No opposition filed

Effective date: 20160418

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160209

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160209

REG Reference to a national code

Ref country code: HU

Ref legal event code: AG4A

Ref document number: E027667

Country of ref document: HU

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161028

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160229

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160209

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160209

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 737003

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: HU

Payment date: 20170419

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180210

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502011007319

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240228

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240222

Year of fee payment: 14