EP2918913B1 - Combustion chamber of a gas turbine - Google Patents

Combustion chamber of a gas turbine Download PDF

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Publication number
EP2918913B1
EP2918913B1 EP15158432.3A EP15158432A EP2918913B1 EP 2918913 B1 EP2918913 B1 EP 2918913B1 EP 15158432 A EP15158432 A EP 15158432A EP 2918913 B1 EP2918913 B1 EP 2918913B1
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EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
accordance
wall
end area
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EP15158432.3A
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German (de)
French (fr)
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EP2918913A1 (en
Inventor
Miklós Dr.-Ing. Gerendás
Carsten Dr.-Ing. Clemen
Thomas Dr.-Ing. Dörr
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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    • 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
    • F23R3/60—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

Definitions

  • the invention relates to the combustion chamber of a gas turbine.
  • the combustion chamber has an outer combustion chamber wall and an inner combustion chamber wall.
  • the inner, hot combustion chamber wall on the outer, cold combustion chamber wall in a suitable manner.
  • the two combustion chamber walls are spaced apart from one another in order to create a gap for the flow of cooling air.
  • the outer, cold combustion chamber wall in this case has a plurality of impingement cooling holes, through which cooling air impinges on the side facing away from the combustion chamber interior side of the inner, hot combustion chamber wall in order to cool them.
  • the inner, hot combustor wall is provided with a plurality of effusion holes through which cooling air exits which abuts the surface of the inner combustor wall to cool and shield it from the hot combustion gases.
  • Such combustion chambers are arranged between a high-pressure compressor and a high-pressure turbine.
  • the outer, cold combustion chamber wall which forms a support structure, is usually produced by welding prefabricated parts. At the discharge area of the combustion chamber, flanges and combustion chamber suspensions made as separate forgings are welded to support the combustion chamber.
  • the combustion chamber walls themselves are usually designed as sheet metal construction.
  • a combustion chamber head is provided with a base plate usually made as a casting.
  • the inner, hot combustion chamber wall is then inserted.
  • This usually consists of shingles, which are formed like a segment. The shingles are formed as castings and have cast-stud bolts, which are guided by recesses of the outer combustion chamber wall and screwed from the outside via nuts.
  • the cooling of the shingles in the vicinity of the studs can not be optimally designed because of the material accumulations occurring there. Thus occur at the transition areas from the shingles to the stud higher temperatures that exceed the temperatures in the rest of the shingles.
  • a seal or sealing lip is provided in the region of the outlet nozzle of the combustion chamber, which seals the exhaust gas jet to the surrounding components and feeds them to the guide vanes of the high-pressure turbine. These sealing lips wear out when the shingles become loose or the shingles vibrate. It proves to be disadvantageous that the sealing lip is formed as part of the support structure of the combustion chamber and can not be replaced in a simple manner.
  • the US 4,628,694 A. discloses a double-walled combustion chamber, which is occupied by shingles, which are mounted at their front region and at its end region respectively in annular grooves of the outer combustion chamber wall.
  • combustion chamber construction is from the EP 2 402 659 A1 known.
  • a single-wall combustion chamber is shown, which is fixed at its rear end region to a housing surrounding the combustion chamber construction.
  • combustion chamber construction is from the WO 2011/070273 A1 previously known.
  • the combustion chamber described therein has an integrally formed with a top plate wall, which is integrally connected at its rear end with a rear Brennschflansch.
  • a similar construction also shows the US 2005/0086945 A1 , In this case also a single-wall combustion chamber is shown, which is slidably mounted on a combustion chamber head and fixed with its rear end to a wall of the gas turbine.
  • the invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a high level of reliability and a long service life with a simple structure and simple, cost-effective manufacturability.
  • Assigns combustion chamber head is held.
  • the inner combustion chamber wall is fixed to the outer combustion chamber wall.
  • the groove is formed between the outer combustion chamber wall and a heat shield.
  • the first, cold combustion chamber wall as is known from the prior art, namely as a joined sheet metal part.
  • the internal second, hot combustion chamber wall can be made of a sheet material or in the form of cast segments or shingles.
  • the inner combustion chamber wall shingles
  • This fixation can according to the invention, for example, by screws or a 360 ° extending clamping ring or similar solutions, such as claws done. According to the invention, there is thus a positive fixing at the rear area of the inner combustion chamber wall.
  • the inner combustion chamber wall is formed segmented, wherein the segments can extend over the entire length of the combustion chamber.
  • the front end region of the inner combustion chamber wall is formed like a seal, for example by means of an additional annular flange or the like.
  • a seal is additionally ensured, but does not affect the longitudinal displacement of the front end portion of the inner combustion chamber wall.
  • the attachment or fixation of the rear end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example by means of screws, which are arranged radially or axially relative to the direction of flow or a central axis of the combustion chamber.
  • An essential advantage of the invention results from the fact that the cooling of the inner combustion chamber wall can be optimally designed over its entire surface. There no Stud bolts are present, there are no restrictions on the heat transfer.
  • Another advantage of a preferred embodiment of the invention is that it is possible to form the sealing lip to the outlet nozzle vane ring so that it can be renewed with an exchange of the inner combustion chamber wall, without the entire combustion chamber construction is affected.
  • the gas turbine engine 110 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.
  • the intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 in an annular flow passage through the compressors 113, 114 protrude.
  • the compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disk 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar stages, comprising an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124 projecting outwardly from a rotatable hub 126.
  • the Fig. 2 shows a longitudinal sectional view of a known from the prior art combustion chamber wall in an enlarged view.
  • a combustion chamber 1 with a central axis 25 is shown, which comprises a combustion chamber head 3, a base plate 8 and a heat shield 2.
  • a burner seal is provided with the reference numeral 4.
  • the combustion chamber 1 has an outer cold combustion chamber wall 7, to which an inner, hot combustion chamber wall 6 is attached.
  • mixed air Zumischlöcher 5 provided for supplying mixed air Zumischlöcher 5 provided.
  • the presentation of impingement cooling holes and effusion holes has been omitted for clarity.
  • the inner combustion chamber wall 6 is provided with bolts 13, which are designed as threaded bolts and are screwed by means of nuts 14.
  • a sealing lip 20 is provided for a strip seal to the outlet nozzle guide vane.
  • the Fig. 3 shows a first example of a combustion chamber, which is not part of the invention.
  • the combustion chamber is basically constructed as in Fig. 2 shown combustion chamber. This means that it also has an outer cold combustion chamber wall 7 and an inner, hot combustion chamber wall 6.
  • the storage is also via combustion chamber suspensions 11 and combustion chamber flanges 12. Also, the sealing lip 20 is shown accordingly.
  • a combustion chamber head 3 At the front end, a combustion chamber head 3, a heat shield 2, a base plate 8 and a burner seal 4 are provided.
  • a groove 16 is formed on the base plate 8, in which a front end 15 of the inner combustion chamber wall 6 is inserted longitudinally displaceable.
  • the rear portion of the inner combustion chamber wall 6 is fixed to the outer combustion chamber wall 7 by means of fastening screws 19 a. In this area, cooling no longer plays such a crucial role, so that this area is not subjected to extreme thermal stress.
  • the base plate 8 has an annular groove 16.
  • the groove 16 is the front end of the inner combustion chamber wall 6 inserted longitudinally displaceable.
  • the groove 16 is formed by a circumferential ridge 17, as well as in the embodiment of Fig. 6 is apparent.
  • the groove 16 is incorporated as a circumferential annular groove in the material of the base plate 8.
  • the front end of the inner combustion chamber wall 6 has a ring-like thickening, which serves both for storage and for sealing.
  • an impingement cooling hole 9 and an effusion hole 10 are shown.
  • Fig. 5 is the head-side end 15 of the inner combustion chamber wall 6 also formed as a circumferential ring land and also serves for sealing and support.
  • the reference numeral 24 designates an additional air hole in the base plate 8.
  • Fig. 6 shows an angled configuration of the head-side end 15 of the inner combustion chamber wall 6. This is mounted in the groove 16 formed by the circumferential ridge 17.
  • Fig. 7 to 12 show different embodiments of the rear bearing of the inner combustion chamber wall 6.
  • a solution is shown in which a fastening screw 19a is screwed in the radial direction.
  • the sealing lip 20 is formed on the outer combustion chamber wall 7.
  • the Fig. 8 an embodiment in which the sealing lip 20 is formed on the inner combustion chamber wall 6 and has an angled ring shape, which rests against the end of the outer combustion chamber wall 7.
  • the fastening screw 19b is inserted in the axial direction in each case.
  • the inner combustion chamber wall 6 is formed angled.
  • the Fig. 10 shows a design variant in which two sealing lips 20 are provided.
  • an additional clamping ring 21 is provided, which is designed as a peripheral ring or can be configured as a segmented claw. According to Fig. 11 the clamping ring 21 carries the
  • Fig. 13 shows an inventive embodiment in an analogous representation to Fig. 3 ,
  • the front, head-side end 15 of the inner, hot combustion chamber wall 6 between the outer, cold combustion chamber wall 7 and the heat shield 2 is guided longitudinally displaceable in a slot formed between these components.
  • the outer cold combustion chamber wall 7 can be constructed conventionally.
  • the inner (hot) combustion chamber wall 6 is formed of sheet metal (360 °) or (possibly cast or sintered) segments (or shingles), which are characterized in that the hot gas side panel front between the base plate 8 or the cold combustion chamber wall 7 and the Heat shield 2 is guided around the burner so that a longitudinal displacement is possible.
  • the hot combustion chamber wall 6 is fixed, for example by screws or a clamping ring (360 °) or claws (individual segments). Since a cavity 29 must be formed between the two combustion chamber walls 6, 7, it is advantageous to thicken the head-side end 15 of the shingle 6 in order to set this distance.
  • FIGS. 14 and 15 are shown a variety of design variants for this purpose.
  • a support ring 28 is formed, which supports the inner combustion chamber wall 6.
  • Fig. 14 is the head end 15 thickened formed, as well as in Fig. 4 shown.
  • the Fig. 15 shows a variant of the bent portion 26, while the Fig. 16 represents a wave stamping. Similar details can also be introduced in the cast or sintered variant. Also at the turbine end of the hot combustion chamber wall 6, the distance to the cold side must be bridged.
  • a step can be embossed in the hot side, so that the attachment (ring or segment) is not exposed as a projecting stage of hot gas flow, as in the FIGS. 17 and 18 is shown.
  • a circumferential groove could also be used be introduced hot gas component, so that the retaining clip does not carry the full temperature load and thus can be made of a cheaper material.

Description

Die Erfindung bezieht sich auf die Brennkammer einer Gasturbine. Die Brennkammer weist eine äußere Brennkammerwand sowie eine innere Brennkammerwand auf.The invention relates to the combustion chamber of a gas turbine. The combustion chamber has an outer combustion chamber wall and an inner combustion chamber wall.

Aus dem Stand der Technik ist es bekannt, die innere, heiße Brennkammerwand an der äußeren, kalten Brennkammerwand in geeigneter Weise zu lagern. Die beiden Brennkammerwände sind dabei voneinander beabstandet, um einen Zwischenraum zur Durchströmung von Kühlluft zu schaffen. Die äußere, kalte Brennkammerwand weist dabei eine Vielzahl von Prallkühllöchern auf, durch welche Kühlluft auf die dem Brennkammerinnenraum abgewandte Seite der inneren, heißen Brennkammerwand auftrifft, um diese zu kühlen. Die innere, heiße Brennkammerwand ist mit einer Vielzahl von Effusionslöchern versehen, durch welche Kühlluft austritt, welche sich an die Oberfläche der inneren Brennkammerwand anlegt, um diese zu kühlen und gegenüber den heißen Verbrennungsgasen abzuschirmen.From the prior art it is known to store the inner, hot combustion chamber wall on the outer, cold combustion chamber wall in a suitable manner. The two combustion chamber walls are spaced apart from one another in order to create a gap for the flow of cooling air. The outer, cold combustion chamber wall in this case has a plurality of impingement cooling holes, through which cooling air impinges on the side facing away from the combustion chamber interior side of the inner, hot combustion chamber wall in order to cool them. The inner, hot combustor wall is provided with a plurality of effusion holes through which cooling air exits which abuts the surface of the inner combustor wall to cool and shield it from the hot combustion gases.

Derartige Brennkammern sind zwischen einem Hochdruckverdichter und einer Hochdruckturbine angeordnet.Such combustion chambers are arranged between a high-pressure compressor and a high-pressure turbine.

Die äußere, kalte Brennkammerwand, welche eine Tragstruktur bildet, wird üblicherweise durch Verschweißen vorgefertigter Teile hergestellt. Am Ausströmbereich der Brennkammer werden Flansche und Brennkammeraufhängungen, welche als separate Schmiedeteile gefertigt sind, angeschweißt, um die Brennkammer zu lagern. Die Brennkammerwände selbst sind üblicherweise als Blechkonstruktion ausgeführt. Am vorderen Ende der Brennkammer ist ein Brennkammerkopf mit einer üblicherweise als Gussteil hergestellten Grundplatte vorgesehen. In dem Innenraum dieser äußeren, kalten Brennkammerwand wird dann die innere, heiße Brennkammerwand eingefügt. Diese besteht üblicherweise aus Schindeln, welche segmentartig ausgebildet sind. Die Schindeln sind als Gussteile ausgebildet und weisen angegossene Stehbolzen auf, welche durch Ausnehmungen der äußeren Brennkammerwand geführt und von außen über Muttern verschraubt werden.The outer, cold combustion chamber wall, which forms a support structure, is usually produced by welding prefabricated parts. At the discharge area of the combustion chamber, flanges and combustion chamber suspensions made as separate forgings are welded to support the combustion chamber. The combustion chamber walls themselves are usually designed as sheet metal construction. At the front end of the combustion chamber, a combustion chamber head is provided with a base plate usually made as a casting. In the interior of this outer, cold combustion chamber wall, the inner, hot combustion chamber wall is then inserted. This usually consists of shingles, which are formed like a segment. The shingles are formed as castings and have cast-stud bolts, which are guided by recesses of the outer combustion chamber wall and screwed from the outside via nuts.

Derartige Konstruktionen sind beispielsweise aus der US 5,435,139 A oder der US 5,758,503 A vorbekannt. Ferner sind aus der US 4,628,694 B und der EP 1 491 823 A1 eine Brennkammer mit den Merkmalen des Oberbegriffs des Anspruchs 1 bekannt.Such constructions are for example from the US 5,435,139 A or the US 5,758,503 A previously known. Furthermore, from the US 4,628,694 B and the EP 1 491 823 A1 a combustion chamber having the features of the preamble of claim 1.

Bei den aus dem Stand der Technik bekannten Lösungen werden somit stets Stehbolzen verwendet, um die innere Brennkammerwand (die Schindeln) zu befestigen. Um diese Befestigung funktionsgerecht durchzuführen, ist es erforderlich, die Stehbolzen mittels der Muttern vorzuspannen. Durch die hohe Temperatur auf der Seite der heißen, inneren Brennkammerwand, wird jedoch der Werkstoff der Stehbolzen so beansprucht, dass der Werkstoff kriecht. Hierdurch baut sich die Vorspannung der Stehbolzen ab. Als Folge treten Vibrationen der Schindeln der inneren Brennkammerwand auf. Dies kann zum Versagen der Befestigung der Schindeln führen und die gesamte Gasturbine zerstören.In the solutions known from the prior art, stud bolts are thus always used to fasten the inner combustion chamber wall (the shingles). To perform this attachment functionally, it is necessary to bias the studs by means of the nuts. Due to the high temperature on the side of the hot, inner combustion chamber wall, however, the material of the stud is claimed so that the material creeps. As a result, the bias of the studs is reduced. As a result, vibrations of the shingles of the inner combustion chamber wall occur. This can lead to the failure of the attachment of the shingles and destroy the entire gas turbine.

Die Kühlung der Schindeln in der Nähe der Stehbolzen kann wegen der dort auftretenden Materialanhäufungen nicht optimal gestaltet werden. Somit treten an den Übergangsbereichen von den Schindeln zu den Stehbolzen höhere Temperaturen auf, die die Temperaturen im restlichen Bereich der Schindeln übertreffen.The cooling of the shingles in the vicinity of the studs can not be optimally designed because of the material accumulations occurring there. Thus occur at the transition areas from the shingles to the stud higher temperatures that exceed the temperatures in the rest of the shingles.

Ein weiterer Nachteil der vorbekannten Lösungen besteht darin, dass im Bereich der Austrittsdüse der Brennkammer eine Dichtung oder Dichtlippe vorgesehen ist, welche den Abgasstrahl zu den umgebenden Bauteilen hin abdichtet und diesen zu den Leitschaufeln der Hochdruckturbine zuführt. Diese Dichtlippen verschleißen bei Lockerung der Schindeln oder bei Vibrationen der Schindeln. Dabei erweist es sich als nachteilig, dass die Dichtlippe als Teil der Tragstruktur der Brennkammer ausgebildet ist und nicht in einfacher Weise ausgetauscht werden kann.Another disadvantage of the previously known solutions is that a seal or sealing lip is provided in the region of the outlet nozzle of the combustion chamber, which seals the exhaust gas jet to the surrounding components and feeds them to the guide vanes of the high-pressure turbine. These sealing lips wear out when the shingles become loose or the shingles vibrate. It proves to be disadvantageous that the sealing lip is formed as part of the support structure of the combustion chamber and can not be replaced in a simple manner.

Die US 4 628 694 A offenbart eine doppelwandige Brennkammer, welche mit Schindeln belegt ist, die an ihrem vorderen Bereich und an ihrem Endbereich jeweils in Ringnuten der äußeren Brennkammerwand gelagert sind.The US 4,628,694 A. discloses a double-walled combustion chamber, which is occupied by shingles, which are mounted at their front region and at its end region respectively in annular grooves of the outer combustion chamber wall.

Eine weitere Brennkammerkonstruktion ist aus der EP 2 402 659 A1 bekannt. Dabei ist eine einwandige Brennkammer dargestellt, welche an ihrem hinteren Endbereich an einem die Brennkammerkonstruktion umgebenden Gehäuse fixiert ist.Another combustion chamber construction is from the EP 2 402 659 A1 known. In this case, a single-wall combustion chamber is shown, which is fixed at its rear end region to a housing surrounding the combustion chamber construction.

Eine weitere Brennkammerkonstruktion ist aus der WO 2011/070273 A1 vorbekannt. Die dort beschriebene Brennkammer weist eine einstückig mit einer Kopfplatte ausgebildete Wandung auf, welche an ihrem rückseitigen Ende einstückig mit einem hinteren Brennkammerflansch verbunden ist.Another combustion chamber construction is from the WO 2011/070273 A1 previously known. The combustion chamber described therein has an integrally formed with a top plate wall, which is integrally connected at its rear end with a rear Brennkammerflansch.

Eine ähnliche Konstruktion zeigt auch die US 2005/0086945 A1 . Dabei ist ebenfalls eine einwandige Brennkammer gezeigt, welche verschiebbar an einem Brennkammerkopf gelagert und mit ihrem hinteren Ende an einer Wandung der Gasturbine fixiert ist.A similar construction also shows the US 2005/0086945 A1 , In this case also a single-wall combustion chamber is shown, which is slidably mounted on a combustion chamber head and fixed with its rear end to a wall of the gas turbine.

Der Erfindung liegt die Aufgabe zugrunde, eine Brennkammer einer Gasturbine der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit ein hohes Maß an Betriebssicherheit und eine hohe Lebensdauer aufweist.The invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a high level of reliability and a long service life with a simple structure and simple, cost-effective manufacturability.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, dass die innere Brennkammerwand an ihrem vorderen Endbereich, bezogen auf die Durchströmungsrichtung der Brennkammer, längs verschiebbar in einer Nut im Bereich einer Grundplatte, welche einemAccording to the invention it is thus provided that the inner combustion chamber wall at its front end, relative to the flow direction of the combustion chamber, longitudinally displaceable in a groove in the region of a base plate, which a

Brennkammerkopf zuordnet ist, gehalten ist. An ihrem hinteren Endbereich ist die innere Brennkammerwand an der äußeren Brennkammerwand fixiert. Die Nut ist zwischen der äußeren Brennkammerwand und einem Hitzeschild ausgebildet.Assigns combustion chamber head is held. At its rear end region, the inner combustion chamber wall is fixed to the outer combustion chamber wall. The groove is formed between the outer combustion chamber wall and a heat shield.

Bei der erfindungsgemäßen Lösung ist es möglich, die erste, kalte Brennkammerwand so auszubilden, wie dies aus dem Stand der Technik bekannt ist, nämlich als gefügtes Blechteil. Die innenliegende zweite, heiße Brennkammerwand kann aus einem Blechmaterial oder in Form von gegossenen Segmenten oder Schindeln hergestellt werden. Durch die Lagerung in einer Nut an der Grundplatte ist es möglich, eine Längsverschiebbarkeit zu ermöglichen, welche insbesondere auch thermische Ausdehnungen zulässt, ohne dass die Gefahr von Beschädigungen besteht. Am hinteren Ende ist die innere Brennkammerwand (Schindel) in der Nähe der Hochdruckturbine fixiert. Diese Fixierung kann erfindungsgemäß beispielsweise durch Schrauben oder einen sich um 360° erstreckenden Klemmring oder ähnliche Lösungen, beispielsweise Krallen, erfolgen. Erfindungsgemäß liegt somit am hinteren Bereich der inneren Brennkammerwand eine formschlüssige Fixierung vor.In the solution according to the invention, it is possible to form the first, cold combustion chamber wall, as is known from the prior art, namely as a joined sheet metal part. The internal second, hot combustion chamber wall can be made of a sheet material or in the form of cast segments or shingles. By mounting in a groove on the base plate, it is possible to allow a longitudinal displacement, which in particular also allows thermal expansion without the risk of damage. At the rear end, the inner combustion chamber wall (shingles) is fixed near the high-pressure turbine. This fixation can according to the invention, for example, by screws or a 360 ° extending clamping ring or similar solutions, such as claws done. According to the invention, there is thus a positive fixing at the rear area of the inner combustion chamber wall.

In günstiger Weiterbildung der Erfindung kann vorgesehen sein, dass die innere Brennkammerwand segmentiert ausgebildet ist, wobei sich die Segmente über die gesamte Länge der Brennkammer erstrecken können.In a favorable development of the invention it can be provided that the inner combustion chamber wall is formed segmented, wherein the segments can extend over the entire length of the combustion chamber.

Besonders günstig kann es sein, wenn der vordere Endbereich der inneren Brennkammerwand dichtungsartig ausgebildet ist, beispielsweise mittels eines zusätzlichen Ringflansches oder ähnlichem. Hierdurch wird zusätzlich eine Abdichtung gewährleistet, die jedoch die Längsverschiebbarkeit des vorderen Endbereichs der inneren Brennkammerwand nicht beeinträchtigt.It may be particularly favorable when the front end region of the inner combustion chamber wall is formed like a seal, for example by means of an additional annular flange or the like. As a result, a seal is additionally ensured, but does not affect the longitudinal displacement of the front end portion of the inner combustion chamber wall.

Die Befestigung oder Fixierung des hinteren Endes der Brennkammerwand kann in günstiger Weise den jeweiligen baulichen Anforderungen angepasst werden, beispielsweise durch Schrauben, welche, bezogen auf die Durchströmungsrichtung oder eine Mittelsachse der Brennkammer radial oder axial angeordnet sind.The attachment or fixation of the rear end of the combustion chamber wall can be adapted in a favorable manner to the respective structural requirements, for example by means of screws, which are arranged radially or axially relative to the direction of flow or a central axis of the combustion chamber.

Als wesentlicher Vorteil ergibt sich erfindungsgemäß, dass die Kühlung der inneren Brennkammerwand auf ihrer gesamten Fläche optimal gestaltet werden kann. Da keine Stehbolzen vorhanden sind, ergeben sich auch keine Einschränkungen hinsichtlich der Wärmeübertragung.An essential advantage of the invention results from the fact that the cooling of the inner combustion chamber wall can be optimally designed over its entire surface. There no Stud bolts are present, there are no restrictions on the heat transfer.

Ein weiterer Vorteil einer bevorzugten Ausgestaltung der Erfindung liegt darin, dass es möglich ist, die Dichtlippe zum Austrittsdüsenleitschaufelring so auszubilden, dass diese bei einem Austausch der inneren Brennkammerwand mit erneuert werden kann, ohne dass die gesamte Brennkammerkonstruktion betroffen ist.Another advantage of a preferred embodiment of the invention is that it is possible to form the sealing lip to the outlet nozzle vane ring so that it can be renewed with an exchange of the inner combustion chamber wall, without the entire combustion chamber construction is affected.

Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung;
Fig. 2
eine Längs-Schnittansicht einer Brennkammer gemäß dem Stand der Technik;
Fig. 3
eine Ansicht, analog Fig. 2, eines ersten Beispiels, welches nicht Teil der Erfindung ist;
Fig. 4 bis 6
unterschiedliche Ausführungsformen der vorderen Lagerung der inneren Brennkammerwand, welche nicht Teil der Erfindung sind;
Fig. 7 bis 12
unterschiedliche Ausgestaltungsformen der hinteren Lagerung der Brennkammerwand;
Fig. 13
eine Ansicht, analog der Fig. 3, eines Ausführungsbeispiels der Erfindung;
Fig. 14 bis 16
unterschiedliche Ausführungsformen der vorderen Lagerung der inneren Brennkammerwand; und
Fig. 17 und 18
unterschiedliche Ausgestaltungsformen der hinteren Lagerung der Brennkammerwand.
In the following the invention will be described by means of embodiments in conjunction with the drawing. Showing:
Fig. 1
a schematic representation of a gas turbine engine according to the present invention;
Fig. 2
a longitudinal sectional view of a combustion chamber according to the prior art;
Fig. 3
a view, analog Fig. 2 a first example, which is not part of the invention;
4 to 6
different embodiments of the front bearing of the inner combustion chamber wall, which are not part of the invention;
Fig. 7 to 12
different embodiments of the rear storage of the combustion chamber wall;
Fig. 13
a view analogous to Fig. 3 , an embodiment of the invention;
Fig. 14 to 16
different embodiments of the front bearing of the inner combustion chamber wall; and
FIGS. 17 and 18
different embodiments of the rear storage of the combustion chamber wall.

Das Gasturbinentriebwerk 110 gemäß Fig. 1 ist ein allgemein dargestelltes Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Das Triebwerk 110 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 111, einen in einem Gehäuse umlaufenden Fan 112, einen Mitteldruckkompressor 113, einen Hochdruckkompressor 114, eine Brennkammer 115, eine Hochdruckturbine 116, eine Mitteldruckturbine 117 und eine Niederdruckturbine 118 sowie eine Abgasdüse 119, die sämtlich um eine zentrale Triebwerksmittelachse 101 angeordnet sind.The gas turbine engine 110 according to Fig. 1 is a generalized example of a turbomachine, in which the invention can be applied. The engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.

Der Mitteldruckkompressor 113 und der Hochdruckkompressor 114 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 120 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 121 in einem ringförmigen Strömungskanal durch die Kompressoren 113, 114 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 122 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 125 vorstehen, die mit Naben 126 der Hochdruckturbine 116 bzw. der Mitteldruckturbine 117 gekoppelt sind.The intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 in an annular flow passage through the compressors 113, 114 protrude. The compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disk 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.

Die Turbinenabschnitte 116, 117, 118 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 123, die radial nach innen vom Gehäuse 121 in den ringförmigen Strömungskanal durch die Turbinen 116, 117, 118 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 124, die nach außen von einer drehbaren Nabe 126 vorstehen. Die Kompressortrommel oder Kompressorscheibe 125 und die darauf angeordneten Schaufeln 122 sowie die Turbinenrotornabe 126 und die darauf angeordneten Turbinenlaufschaufeln 124 drehen sich im Betrieb um die Triebwerksmittelachse 101.The turbine sections 116, 117, 118 have similar stages, comprising an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124 projecting outwardly from a rotatable hub 126. The compressor drum or compressor disk 125 and the vanes 122 disposed thereon, as well as the turbine rotor hub 126 and the turbine blades 124 disposed thereon, rotate about the engine centerline 101 during operation.

Die Fig. 2 zeigt eine Längs-Schnittansicht einer aus dem Stand der Technik bekannten Brennkammerwand in vergrößerter Darstellung. Dabei ist eine Brennkammer 1 mit einer Mittelachse 25 dargestellt, welche einen Brennkammerkopf 3, eine Grundplatte 8 und ein Hitzeschild 2 umfasst. Eine Brennerdichtung ist mit dem Bezugszeichen 4 versehen. Die Brennkammer 1 weist eine äußere kalte Brennkammerwand 7 auf, an welcher eine innere, heiße Brennkammerwand 6 befestigt ist. Zur Zuführung von Mischluft sind Zumischlöcher 5 vorgesehen. Auf die Darstellung von Prallkühllöchern und Effusionslöchern wurde der Übersichtlichkeit halber verzichtet.The Fig. 2 shows a longitudinal sectional view of a known from the prior art combustion chamber wall in an enlarged view. In this case, a combustion chamber 1 with a central axis 25 is shown, which comprises a combustion chamber head 3, a base plate 8 and a heat shield 2. A burner seal is provided with the reference numeral 4. The combustion chamber 1 has an outer cold combustion chamber wall 7, to which an inner, hot combustion chamber wall 6 is attached. For supplying mixed air Zumischlöcher 5 provided. The presentation of impingement cooling holes and effusion holes has been omitted for clarity.

Die innere Brennkammerwand 6 ist mit Bolzen 13 versehen, welche als Gewindebolzen ausgeführt sind und mittels Muttern 14 verschraubt sind. Am ausströmseitigen Ende der Brennkammer 1 ist eine Dichtlippe 20 für eine Streifendichtung zur Austrittsdüsenleitschaufel vorgesehen. Die Lagerung der Brennkammer 1 erfolgt über Brennkammerflansche 12 und Brennkammeraufhängungen 11.The inner combustion chamber wall 6 is provided with bolts 13, which are designed as threaded bolts and are screwed by means of nuts 14. At the outlet end of the combustion chamber 1, a sealing lip 20 is provided for a strip seal to the outlet nozzle guide vane. The storage of the combustion chamber 1 via Brennkammerflansche 12 and 11 Brennkammeraufhängungen.

In den folgenden Ausführungsbeispielen sind gleiche Teile mit gleichen Bezugsziffern versehen. Gleiche Teile und gleiche Lösungsaspekte sind bei den unterschiedlichen Ausführungsbeispielen nicht jeweils nochmals detailliert beschrieben, es wird diesbezüglich auf den Text der anderen Ausführungsbeispiele verwiesen.In the following embodiments, like parts are given the same reference numerals. The same parts and the same solution aspects are not described again in detail in the different embodiments, reference is made in this regard to the text of the other embodiments.

Die Fig. 3 zeigt ein erstes Beispiel einer Brennkammer, welche nicht Teil der Erfindung ist. Die Brennkammer ist grundsätzlich so aufgebaut, wie die in Fig. 2 gezeigte Brennkammer. Dies bedeutet, dass sie ebenfalls eine äußere kalte Brennkammerwand 7 sowie eine innere, heiße Brennkammerwand 6 aufweist. Die Lagerung erfolgt ebenfalls über Brennkammeraufhängungen 11 und Brennkammerflansche 12. Auch die Dichtlippe 20 ist entsprechend dargestellt. Am vorderen Ende ist ein Brennkammerkopf 3, ein Hitzeschild 2, eine Grundplatte 8 und eine Brennerdichtung 4 vorgesehen.The Fig. 3 shows a first example of a combustion chamber, which is not part of the invention. The combustion chamber is basically constructed as in Fig. 2 shown combustion chamber. This means that it also has an outer cold combustion chamber wall 7 and an inner, hot combustion chamber wall 6. The storage is also via combustion chamber suspensions 11 and combustion chamber flanges 12. Also, the sealing lip 20 is shown accordingly. At the front end, a combustion chamber head 3, a heat shield 2, a base plate 8 and a burner seal 4 are provided.

Bei diesem Beispiel ist an der Grundplatte 8 eine Nut 16 ausgebildet, in welche ein vorderes Ende 15 der inneren Brennkammerwand 6 längsverschiebbar eingeführt ist.In this example, a groove 16 is formed on the base plate 8, in which a front end 15 of the inner combustion chamber wall 6 is inserted longitudinally displaceable.

Der hintere Bereich der inneren Brennkammerwand 6 ist mittels Befestigungsschrauben 19a an der äußeren Brennkammerwand 7 fixiert. In diesem Bereich spielt die Kühlung keine so entscheidende Rolle mehr, so dass dieser Bereich thermisch nicht extrem beansprucht wird.The rear portion of the inner combustion chamber wall 6 is fixed to the outer combustion chamber wall 7 by means of fastening screws 19 a. In this area, cooling no longer plays such a crucial role, so that this area is not subjected to extreme thermal stress.

Die Fig. 4 bis 6 zeigen jeweils unterschiedliche Ausgestaltungsvarianten der Befestigung der inneren Brennkammerwand 6 an der Grundplatte 8. Bei allen drei Ausführungsbeispielen weist die Grundplatte 8 eine Ringnut 16 auf. In die Ringnut 16 ist
das vordere Ende der inneren Brennkammerwand 6 längsverschiebbar eingeführt. Bei dem in Fig. 4 gezeigten Ausführungsbeispiel wird die Nut 16 durch einen umlaufenden Steg 17 gebildet, so wie dies auch in dem Ausführungsbeispiel der Fig. 6 ersichtlich ist. Bei dem Ausführungsbeispiel der Fig. 5 ist die Nut 16 als umlaufende Ringnut in das Material der Grundplatte 8 eingearbeitet. Bei dem Ausführungsbeispiel der Fig. 4 weist das vordere Ende der inneren Brennkammerwand 6 eine ringartige Verdickung auf, welche sowohl zur Lagerung als auch zur Abdichtung dient. In schematischer Darstellung ist ein Prallkühlloch 9 und ein Effusionsloch 10 dargestellt.The 4 to 6 show in each case different design variants of the attachment of the inner combustion chamber wall 6 to the base plate 8. In all three embodiments, the base plate 8 has an annular groove 16. In the annular groove 16 is
the front end of the inner combustion chamber wall 6 inserted longitudinally displaceable. At the in Fig. 4 the embodiment shown, the groove 16 is formed by a circumferential ridge 17, as well as in the embodiment of Fig. 6 is apparent. In the embodiment of the Fig. 5 the groove 16 is incorporated as a circumferential annular groove in the material of the base plate 8. In the embodiment of the Fig. 4 the front end of the inner combustion chamber wall 6 has a ring-like thickening, which serves both for storage and for sealing. In a schematic representation, an impingement cooling hole 9 and an effusion hole 10 are shown.

Bei dem Beispiel der Fig. 5 ist das kopfseitige Ende 15 der inneren Brennkammerwand 6 ebenfalls als umlaufender Ring-Steg ausgebildet und dient ebenfalls zur Abdichtung und Abstützung. Das Bezugszeichen 24 bezeichnet ein zusätzliches Luftloch in der Grundplatte 8.In the example of Fig. 5 is the head-side end 15 of the inner combustion chamber wall 6 also formed as a circumferential ring land and also serves for sealing and support. The reference numeral 24 designates an additional air hole in the base plate 8.

Das Beispiel der Fig. 6 zeigt eine abgewinkelte Ausgestaltung des kopfseitigen Endes 15 der inneren Brennkammerwand 6. Dieses ist in der durch den umlaufenden Steg 17 gebildeten Nut 16 gelagert.The example of Fig. 6 shows an angled configuration of the head-side end 15 of the inner combustion chamber wall 6. This is mounted in the groove 16 formed by the circumferential ridge 17.

Die Fig. 7 bis 12 zeigen unterschiedliche Ausgestaltungsformen der hinteren Lagerung der inneren Brennkammerwand 6. In Fig. 7 ist eine Lösung gezeigt, bei welcher eine Befestigungsschraube 19a in radialer Richtung eingeschraubt ist. Die Dichtlippe 20 ist an der äußeren Brennkammerwand 7 ausgebildet. Als Alternative hierzu zeigt die Fig. 8 ein Ausführungsbeispiel, bei welchem die Dichtlippe 20 an der inneren Brennkammerwand 6 ausgebildet ist und eine abgewinkelte Ringform aufweist, welche sich gegen das Ende der äußeren Brennkammerwand 7 anlegt.The Fig. 7 to 12 show different embodiments of the rear bearing of the inner combustion chamber wall 6. In Fig. 7 a solution is shown in which a fastening screw 19a is screwed in the radial direction. The sealing lip 20 is formed on the outer combustion chamber wall 7. As an alternative to this shows the Fig. 8 an embodiment in which the sealing lip 20 is formed on the inner combustion chamber wall 6 and has an angled ring shape, which rests against the end of the outer combustion chamber wall 7.

Bei den Ausführungsbeispielen der Fig. 9 bis 12 ist die Befestigungsschraube 19b jeweils in Axialrichtung eingeführt. Hierzu ist die innere Brennkammerwand 6 abgewinkelt ausgebildet. Die Fig. 10 zeigt eine Ausgestaltungsvariante, bei welcher zwei Dichtlippen 20 vorgesehen sind.In the embodiments of the Fig. 9 to 12 the fastening screw 19b is inserted in the axial direction in each case. For this purpose, the inner combustion chamber wall 6 is formed angled. The Fig. 10 shows a design variant in which two sealing lips 20 are provided.

Bei den Ausführungsbeispielen gemäß den Fig. 11 und 12 ist ein zusätzlicher Klemmring 21 vorgesehen, welcher als Umfangsring ausgebildet ist oder als segmentierte Kralle ausgestaltet sein kann. Gemäß Fig. 11 trägt der Klemmring 21 dieIn the embodiments according to the FIGS. 11 and 12 an additional clamping ring 21 is provided, which is designed as a peripheral ring or can be configured as a segmented claw. According to Fig. 11 the clamping ring 21 carries the

Dichtlippe 20. Eine ähnliche Lösung ist in Fig. 12 beschrieben, wobei zusätzlich ein Überhang 23 vorgesehen ist, um den Klemmring 21 oder die Nut 22 vor Heißgasen zu schützen.Sealing lip 20. A similar solution is in Fig. 12 described, in addition, an overhang 23 is provided to protect the clamping ring 21 or the groove 22 from hot gases.

Die Fig. 13 zeigt ein erfindungsgemäßes Ausführungsbeispiel in analoger Darstellung zur Fig. 3. Bei diesem Ausführungsbeispiel ist das vordere, kopfseitige Ende 15 der inneren, heißen Brennkammerwand 6 zwischen der äußeren, kalten Brennkammerwand 7 und dem Hitzeschild 2 in einem zwischen diesen Bauteilen ausgebildeten Schlitz längsverschiebbar geführt.The Fig. 13 shows an inventive embodiment in an analogous representation to Fig. 3 , In this embodiment, the front, head-side end 15 of the inner, hot combustion chamber wall 6 between the outer, cold combustion chamber wall 7 and the heat shield 2 is guided longitudinally displaceable in a slot formed between these components.

Die äußere kalte Brennkammerwand 7 kann konventionell aufgebaut werden. Die innere (heiße) Brennkammerwand 6 wird aus Blech (360°) oder (möglicherweise gegossenen bzw. gesinterten) Segmenten (oder Schindeln) ausgebildet, welche sich dadurch auszeichnen, dass die heißgasseitige Verkleidung vorne zwischen der Grundplatte 8 oder der kalten Brennkammerwand 7 und dem Hitzeschild 2 um den Brenner so geführt wird, dass eine Längsverschieblichkeit ermöglicht wird. Am hinteren Ende (nahe der Turbine) wird die heiße Brennkammerwand 6 fixiert, zum Beispiel durch Schrauben oder einen Klemmring (360°) bzw. Krallen (einzelne Segmente). Da zwischen den beiden Brennkammerwänden 6, 7 ein Hohlraum 29 ausgebildet sein muss, ist es vorteilhaft, das kopfseitige Ende 15 der Schindel 6 aufzudicken, um diesen Abstand einzustellen. Auch kann es vorteilhaft sein, die Bauteiltoleranzen durch eine gewisse radiale Flexibilität auszugleichen. Dies kann durch ein Umbiegen 26 des heißseitigen Bleches in eine C- bzw. U-Form oder durch Einbringen einer Wellenprägung 27 erfolgen. In den Fig. 14 und 15 sind unterschiedlichste Ausgestaltungsvarianten hierzu dargestellt. An dem Hitzeschild 2 ist jeweils ein Stützring 28 ausgeformt, welcher die innere Brennkammerwand 6 abstützt. Gemäß Fig. 14 ist das kopfseitige Ende 15 verdickt ausgebildet, so wie auch in Fig. 4 dargestellt. Die Fig. 15 zeigt eine Variante des umgebogenen Bereichs 26, während die Fig. 16 eine Wellenprägung darstellt. Ähnliche Details können auch bei der gegossenen bzw. gesinterten Variante eingebracht werden. Auch am turbinenseitigen Ende der heißen Brennkammerwand 6 muss der Abstand zur Kaltseite überbrückt werden. Hierzu kann eine Stufe in die heiße Seite eingeprägt werden, so dass die Befestigung (Ring oder Segment) nicht als vorspringende Stufe der Heißgasströmung ausgesetzt wird, so wie dies in den Fig. 17 und 18 gezeigt ist. Alternativ könnte auch eine umlaufende Nut im
heißgasseitigen Bauteil eingebracht werden, so dass die Halteklammer nicht die volle Temperaturlast trägt und somit aus einem preiswerteren Material hergestellt werden kann.The outer cold combustion chamber wall 7 can be constructed conventionally. The inner (hot) combustion chamber wall 6 is formed of sheet metal (360 °) or (possibly cast or sintered) segments (or shingles), which are characterized in that the hot gas side panel front between the base plate 8 or the cold combustion chamber wall 7 and the Heat shield 2 is guided around the burner so that a longitudinal displacement is possible. At the rear end (near the turbine), the hot combustion chamber wall 6 is fixed, for example by screws or a clamping ring (360 °) or claws (individual segments). Since a cavity 29 must be formed between the two combustion chamber walls 6, 7, it is advantageous to thicken the head-side end 15 of the shingle 6 in order to set this distance. It may also be advantageous to compensate for the component tolerances by a certain radial flexibility. This can be done by bending 26 of the hot side sheet in a C- or U-shape or by introducing a corrugation 27. In the FIGS. 14 and 15 are shown a variety of design variants for this purpose. On the heat shield 2 in each case a support ring 28 is formed, which supports the inner combustion chamber wall 6. According to Fig. 14 is the head end 15 thickened formed, as well as in Fig. 4 shown. The Fig. 15 shows a variant of the bent portion 26, while the Fig. 16 represents a wave stamping. Similar details can also be introduced in the cast or sintered variant. Also at the turbine end of the hot combustion chamber wall 6, the distance to the cold side must be bridged. For this purpose, a step can be embossed in the hot side, so that the attachment (ring or segment) is not exposed as a projecting stage of hot gas flow, as in the FIGS. 17 and 18 is shown. Alternatively, a circumferential groove could also be used
be introduced hot gas component, so that the retaining clip does not carry the full temperature load and thus can be made of a cheaper material.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
Brennkammercombustion chamber
22
Hitzeschildheat shield
33
Brennkammerkopfbulkhead
44
BrennerdichtungBrenner seal
55
ZumischlochZumischloch
66
innere, heiße Brennkammerwand/Segment/Schindelinner, hot combustion chamber wall / segment / shingles
77
äußere, kalte Brennkammerwandouter, cold combustion chamber wall
88th
Grundplattebaseplate
99
PrallkühllochImpingement cooling hole
1010
Effusionslocheffusion
1111
Brennkammeraufhängungcombustion chamber suspension
1212
BrennkammerflanschBrennkammerflansch
1313
Bolzenbolt
1414
Muttermother
1515
kopfseitiges Ende der inneren, heißen Brennkammerwand 6Head end of the inner, hot combustion chamber wall. 6
1616
Nut in Grundplatte 8Groove in base plate 8
1717
umlaufender Steg auf Grundplattecircumferential web on base plate
1818
zu Nut 16 bzw. Steg 17 passender Steg an Schindel 6to groove 16 or web 17 matching web on shingles. 6
1919
Befestigungsschraube der Schindel (a: vertikal, b: horizontal)Shingle fixing screw (a: vertical, b: horizontal)
2020
Dichtlippe für Streifendichtung zur Austrittsdüsenleitschaufel (NGV)Sealing lip for strip seal to outlet nozzle guide vane (NGV)
2121
Klemmring (360°) oder -kralle (segmentiert)Clamping ring (360 °) or claw (segmented)
2222
Nut oder Stufe in der inneren, heißen Brennkammerwand 6 zum Eingriff des Klemmrings 21Groove or step in the inner, hot combustion chamber wall 6 for engagement of the clamping ring 21st
2323
Überhang an der inneren, heißen Brennkammerwand 6 zum Schutz von Klemmring und Nut oder Stufe vor den HeißgasenOverhang on the inner, hot combustion chamber wall 6 to protect the clamping ring and groove or step in front of the hot gases
2424
Luftlochair pocket
2525
Mittelachsecentral axis
2626
umgebogener Bereichbent area
2727
Wellenprägungcorrugated structure
2828
Stützringsupport ring
2929
Hohlraumcavity
101101
TriebwerksmittelachseEngine centerline axis
110110
Gasturbinentriebwerk / KerntriebwerkGas turbine engine / core engine
111111
Lufteinlassair intake
112112
Fanfan
113113
Mitteldruckkompressor (Verdichter)Medium pressure compressor (compressor)
114114
HochdruckkompressorHigh pressure compressor
115115
Brennkammercombustion chamber
116116
HochdruckturbineHigh-pressure turbine
117117
MitteldruckturbineIntermediate pressure turbine
118118
NiederdruckturbineLow-pressure turbine
119119
Abgasdüseexhaust nozzle
120120
Leitschaufelnvanes
121121
TriebwerksgehäuseEngine casing
122122
KompressorlaufschaufelnCompressor blades
123123
Leitschaufelnvanes
124124
Turbinenschaufelnturbine blades
125125
Kompressortrommel oder -scheibeCompressor drum or disc
126126
TurbinenrotornabeTurbinenrotornabe
127127
Auslasskonusoutlet cone

Claims (8)

  1. Combustion chamber of a gas turbine having an outer combustion chamber wall (7), an inner combustion chamber wall (6) with a heat shield (2), a combustion chamber head (3) and a base plate (8), where the inner combustion chamber wall (6), at its front end area relative to the direction of flow through the combustion chamber, is held longitudinally movable in a groove (16) provided in the area of the combustion chamber head (3) and the base plate (8) there arranged, and is fixed to the outer combustion chamber wall (7) at its rear outflow-side end area, characterized in that the groove (16) is designed between the outer combustion chamber wall (7) and the heat shield (2).
  2. Combustion chamber in accordance with Claim 1, characterized in that the rear end area is positively fixed.
  3. Combustion chamber in accordance with one of the Claims 1 or 2, characterized in that fixing of the rear end area is provided by means of bolts (19) or by a clamping ring (21) or by means of claws.
  4. Combustion chamber in accordance with one of the Claims 1 to 3, characterized in that the inner combustion chamber wall (6) is designed segmented.
  5. Combustion chamber in accordance with one of the Claims 1 to 4, characterized in that the inner combustion chamber wall (6) is provided with tiles and/ or includes tiles and/ or is designed as a tile.
  6. Combustion chamber in accordance with one of the Claims 1 to 5, characterized in that the front end area of the inner combustion chamber wall (6) forms a seal.
  7. Combustion chamber in accordance with one of the Claims 3 to 6, characterized in that the rear end area of the inner combustion chamber wall (6) is fixed by means of radially arranged or axially arranged bolts (19a, 19b).
  8. Combustion chamber in accordance with Claim 7, characterized in that the bolts (19a, 19b) are arrangeable adjacent to a sealing lip (20), which is part of a seal for an outlet nozzle guide vane.
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Also Published As

Publication number Publication date
EP2918913A1 (en) 2015-09-16
DE102014204481A1 (en) 2015-09-17
US20150260401A1 (en) 2015-09-17
US9506653B2 (en) 2016-11-29

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