EP2503242B1 - Combustion chamber head with holder for burner seals in gas turbines - Google Patents

Combustion chamber head with holder for burner seals in gas turbines Download PDF

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Publication number
EP2503242B1
EP2503242B1 EP12002047.4A EP12002047A EP2503242B1 EP 2503242 B1 EP2503242 B1 EP 2503242B1 EP 12002047 A EP12002047 A EP 12002047A EP 2503242 B1 EP2503242 B1 EP 2503242B1
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EP
European Patent Office
Prior art keywords
combustion chamber
burner
seal
base plate
holder
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EP12002047.4A
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German (de)
French (fr)
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EP2503242A2 (en
EP2503242A3 (en
Inventor
Miklós Dr.-Ing. Gerendás
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • 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 a combustion chamber head of a gas turbine, in particular the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • a seal is shown around a burner of a gas turbine, which is arranged upstream of a base plate of the combustion chamber, projects through it and a heat shield into the combustion chamber and fulfills the same function as described above.
  • the seal can no longer leave its intended place, but can only be moved in the axial direction along the burner.
  • the actual sealing force which is absolutely necessary for generating and maintaining the sealing function, is usually not provided in gas turbine combustion chambers by a spring element, but by the pressure difference between the combustion chamber outside and the combustion chamber inside, which acts on the effective surface of the seal.
  • this anti-rotation device for guiding the burner and its seal is shown, some of which are made in one piece with the base plate of the combustion chamber or are fixed or movably fastened thereon.
  • this anti-rotation device is represented by a sheet metal ring with radial tabs which engage in recesses in adjacent ring-shaped components. These radial tabs are not used as elastic elements during assembly.
  • US 5 222 358 A a system for the releasable mounting of a pre-evaporator pot on a combustion chamber of a gas turbine engine.
  • EP 1 193 451 A2 a combustor head of a gas turbine with a heat shield and a sleeve, which is held in position with holding elements, is known.
  • WO 96/18853 A1 shows a holder of a fuel nozzle of a gas turbine burner.
  • the invention has for its object to provide a combustion chamber head of the type mentioned, which has a simple design and simple, inexpensive to manufacture, a simple design of the burner seal and is simple and inexpensive to assemble.
  • the combustion chamber head has a base plate which is provided with a central recess in which at least one burner is arranged.
  • the base plate is connected at its radially inner and outer areas to walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing).
  • a burner seal sealing the burner to the edge of the recess is provided according to the invention.
  • the burner seal is arranged upstream of the base plate and can be brought into abutment against a collar formed on the base plate and forming the edge of the central recess. This creates a seal between the burner seal and the base plate.
  • a holding element of the burner seal is designed in the form of a ring and is arranged upstream of the burner seal.
  • the annular holding element is in engagement with at least one shoulder of the base plate.
  • This approach can be designed, for example, in the form of a thickening.
  • the ring-shaped holding element is provided with at least one locking tab which engages with the attachment of the base plate (thickening).
  • the tab is preferably arranged on the inner ring of the annular holding element; according to the invention it is also possible to form the tab on the outer ring of the annular holding element.
  • the tab In order to bring the tab into engagement with the extension, it has a recess into which the tab can be inserted, in particular by deforming the tab.
  • the burner seal is funnel-shaped on its upstream side.
  • the seal as in DE 100 48 864 A1 to be provided upstream of the base plate of the combustion chamber, which can be brought to bear on a collar of the base plate which runs around the recess for carrying out the burner seal, and a holder for the burner seal is a simple sheet metal ring with, for example, three outwardly projecting tabs, which are formed in recesses in thickened areas Engage the base plate of the combustion chamber.
  • the burner seal has a feed funnel at the upstream end, which simplifies the assembly of the burner and no longer fulfills any other function during operation.
  • the tabs on the annular seal holder can be attached to the inner or outer edge of the seal holder.
  • the ring-shaped holding element (sheet metal ring) is placed over the burner seal in such a way that the tabs come to rest next to the recesses in the three recesses of the thickened base plate. Then the tabs of the ring-shaped holding element are pressed in the direction of the base plate by a correspondingly shaped tool and the ring-shaped holding element is rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the attachment) of the base plate in such a way that the annular holding element can no longer turn back, but the tabs can spring back into their original shape without being under tension.
  • An anti-twist device for the burner seal itself is not necessary according to general operating experience and is therefore not made possible by the installation described here.
  • the burner seal is kept close to the combustion chamber head during the entire operating time.
  • the sealing force is generated by the pressure difference between the air flowing around the combustion chamber and the air in the combustion chamber and not by the holder of the burner seal. Thanks to the integrated feed hopper, no additional component is required for this function, which in turn would have to be attached reliably and reliably. The costs for the manufacture and assembly of an anti-rotation device are saved since this function is not necessary.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention can be applied. However, it is clear from the following that the invention can also be used in other turbomachinery.
  • the engine 10 is designed in a conventional manner and comprises an air inlet 11, a fan 12 rotating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust gas nozzle in the flow direction 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each comprise a plurality of stages, each of which has a circumferential arrangement of fixed stationary guide vanes 20, which are generally referred to as stator vanes, and which extend radially inward from the engine housing 21 in an annular flow channel through the compressors 13, 14 protrude.
  • the compressors also have an arrangement of compressor blades 22 which protrude radially outward from a rotatable drum or disk 26 which are coupled to hubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17.
  • the turbine sections 16, 17, 18 have similar steps, comprising an arrangement of fixed guide vanes 23 which extend radially inward from the housing 21 into the annular flow channel project through the turbines 16, 17, 18, and a subsequent array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 arranged thereon and the turbine rotor hub 27 and the turbine rotor blades 24 arranged thereon rotate during operation about the engine axis 1.
  • the Fig. 2 shows the area of a combustion chamber 108 of a gas turbine in a simplified schematic representation.
  • This includes an inner combustion chamber housing 109 and an outer combustion chamber housing 110.
  • a combustion chamber head 107 is arranged upstream of the combustion chamber 108, in which a burner 106 with arm and head is arranged.
  • the air supply to the combustion chamber 8 takes place via a front fan 101 (fan) which is driven by a drive shaft 102.
  • a compressor 103 is also connected to the drive shaft 102.
  • Reference numeral 104 shows a bypass flow (bypass flow channel).
  • the incoming air is directed via a compressor outlet stator 105 with a diffuser.
  • the flow emerging from the combustion chamber 108 is carried out by a turbine stator 111 and a turbine impeller 112.
  • the Fig. 3 shows a schematic detailed view of an embodiment of the solution according to the invention.
  • a base plate 113 is arranged on the upstream end region of the combustion chamber 108 and is provided with a recess which is delimited by a collar 118.
  • the burner 106 is passed through the recess, as shown in FIGS Fig. 1 and 2 is shown.
  • the base plate 113 is provided with an extension 114 (thickening).
  • the thickening 114 supports a burner seal 116 in a recess 115, which is ring-shaped, as is known from the prior art.
  • the burner seal 116 is held by a holding element 117 (holding ring), as is described in the following figures.
  • the Fig. 4 shows a part of the annular base plate 113, which is provided with the collar 118, which delimits the recess 121 for the passage of the burner 106.
  • Distributed around the circumference of the collar 118 are three lugs 114 (thickening of the base plate 113).
  • the Fig. 5 shows a schematic partial side sectional view of the base plate 113 with the collar 118 and an approach 114 with a recess 115.
  • Die Fig. 6 shows the in Fig. 5 Arrangement shown in the assembled state of the annular burner seal 116 and the holding element 117 (retaining ring).
  • the holding element 117 shows a locking tab (tab) 120, as will be described below.
  • the Fig. 6 shows the arrangement of the locking tab 120 on the radially outer region of the retaining ring 117, as shown in the right half of the figure Fig. 8 is shown. There are three locking tabs (tabs) 120 distributed around the circumference.
  • the Fig. 7 shows a variant in which the locking tab 120 is introduced into the recess 115 of the extension 114. The fully assembled state is thus shown.
  • the right half of the picture Fig. 8 shows variants of the locking tabs, namely a locking tab 120a of the seal holder (retaining ring 117).
  • the variant of the locking tab 120b is arranged on the outside of the holding ring 117, while the variant of the locking tab 120c is arranged on the inside of the holding ring 117.
  • the locking tabs 120b and 120c are each shown in the bent state.

Description

Die Erfindung bezieht sich auf einen Brennkammerkopf einer Gasturbine, im Einzelnen bezieht sich die Erfindung dabei auf einen Brennkammerkopf gemäß den Merkmalen des Oberbegriffs des Anspruches 1.The invention relates to a combustion chamber head of a gas turbine, in particular the invention relates to a combustion chamber head according to the features of the preamble of claim 1.

In der DE 44 27 222 A1 ist eine Dichtung um einen Brenner einer Gasturbine beschrieben, welcher stromab einer Grundplatte der Brennkammer angeordnet ist, durch ein Hitzeschild hindurch in die Brennkammer ragt und die Bewegungen zwischen dem Brenner, welcher im Brennkammergehäuse befestigt ist, und der Brennkammer selbst derart ausgleicht, dass keine inakzeptablen Leckagen entstehen. Im engeren Sinne gasdicht braucht diese Art der Dichtung nicht zu sein.In the DE 44 27 222 A1 describes a seal around a burner of a gas turbine, which is arranged downstream of a base plate of the combustion chamber, protrudes through a heat shield into the combustion chamber and compensates for the movements between the burner, which is fastened in the combustion chamber housing, and the combustion chamber itself in such a way that no unacceptable Leaks occur. In the narrower sense, this type of seal need not be gas-tight.

In der DE 100 48 864 A1 wird eine Dichtung um einen Brenner einer Gasturbine dargestellt, welcher stromauf einer Grundplatte der Brennkammer angeordnet ist, durch sie und ein Hitzeschild hindurch in die Brennkammer ragt und die gleiche Funktion erfüllt, wie oben beschrieben.In the DE 100 48 864 A1 a seal is shown around a burner of a gas turbine, which is arranged upstream of a base plate of the combustion chamber, projects through it and a heat shield into the combustion chamber and fulfills the same function as described above.

Sobald der Brenner eingesetzt ist, kann die Dichtung ihren vorgesehenen Platz nicht mehr verlassen, sondern nur noch entlang des Brenners in axialer Richtung verschoben werden. Die eigentliche Dichtkraft, welche zur Erzeugung und Aufrechterhaltung der Dichtfunktion zwingend erforderlich ist, wird bei Gasturbinenbrennkammern üblicherweise nicht durch ein Federelement, sondern durch die Druckdifferenz zwischen der Brennkammeraußenseite und der Brennkammerinnenseite bereitgestellt, welche auf die wirksame Fläche der Dichtung wirkt.As soon as the burner is inserted, the seal can no longer leave its intended place, but can only be moved in the axial direction along the burner. The actual sealing force, which is absolutely necessary for generating and maintaining the sealing function, is usually not provided in gas turbine combustion chambers by a spring element, but by the pressure difference between the combustion chamber outside and the combustion chamber inside, which acts on the effective surface of the seal.

Bevor der Brenner allerdings eingesetzt ist und um sicherzustellen, dass sich die Dichtung beim Starten der Gasturbine nahe der Dichtfläche befindet und dann durch die entstehende Druckdifferenz auch wirklich an die Grundplatte der Brennkammer oder das Hitzeschild gedrückt wird, muss eine Vorrichtung vorgesehen werden, welche die Dichtung nahe der Dichtfläche positioniert, ohne sie anzudrücken. Bei der aus der DE 44 27 222 A1 bekannten Lösung wird die axiale Positionierung durch eine Abstandsscheibe eingestellt, welche sich zwischen der Grundplatte der Brennkammer und der Dichtung befindet. Die radiale Positionierung der Dichtung vor dem Einbau des Brenners wird durch die Form der Ausnehmung in der Grundplatte der Brennkammer sichergestellt. Bei der aus der DE 100 48 864 A1 bekannten Lösung wird die Positionierung der Dichtung in radialer und axialer Richtung durch halbmondförmige Klammern ermöglicht, welche durch die Bolzen des Hitzeschildes gehalten werden.Before the burner is inserted, however, and to ensure that the seal is close to the sealing surface when the gas turbine is started and then is actually pressed against the base plate of the combustion chamber or the heat shield by the pressure difference which arises, a device must be provided which seals the seal positioned near the sealing surface without pressing it. With the from the DE 44 27 222 A1 known solution, the axial positioning is adjusted by a spacer which is located between the base plate of the combustion chamber and the seal. The radial positioning of the seal before installing the Brenner is ensured by the shape of the recess in the base plate of the combustion chamber. With the from the DE 100 48 864 A1 known solution, the positioning of the seal in the radial and axial direction is made possible by crescent-shaped brackets which are held by the bolts of the heat shield.

Einen anderen Lösungsansatz zeigen die US 5,419,115 A und die US 5,463,864 A . Hier wird die Führung und Dichtung des Brenners erst nach dem Hitzeschild von der stromab liegenden Seite des Brennkammerkopfes montiert und danach stromauf des Kopfes durch eine an diese Brenner-Führung gefügte ein- oder zweiteilige Halterung befestigt. Dies geschieht so, dass diese Vorrichtung aus Führung und Halterung noch geringe gleitende Bewegungen in radialer und lateraler Richtung durchführen kann, um wiederum das Einführen des Brenners zu ermöglichen und im Betrieb die Relativbewegungen zwischen Brennkammergehäuse, in welchem der Brenner befestigt ist, und der Brennkammer ausgeglichen werden können. In beiden Schriften werden unterschiedliche Ausformungen einer Verdrehsicherung für die Führung des Brenners und deren Dichtung dargestellt, welche zum Teil einstückig mit der Grundpatte der Brennkammer ausgeführt sind oder fest bzw. beweglich auf dieser befestigt werden. In der US 5,524,438 A wird in einer weiteren Variation diese Verdrehsicherung durch einen Blechring mit radialen Laschen dargestellt, welche in Ausnehmungen benachbarter ringförmiger Bauteile eingreifen. Diese radialen Laschen werden bei der Montage nicht als elastische Elemente verwendet.They show a different approach US 5,419,115 A and the US 5,463,864 A , Here, the guide and seal of the burner are mounted only after the heat shield from the downstream side of the combustion chamber head and then fastened upstream of the head by means of a one-part or two-part holder attached to this burner guide. This is done in such a way that this guide and holder device can still carry out slight sliding movements in the radial and lateral directions, in order in turn to allow the burner to be inserted and, during operation, to compensate for the relative movements between the combustion chamber housing in which the burner is fastened and the combustion chamber can be. In both documents different forms of an anti-rotation device for guiding the burner and its seal are shown, some of which are made in one piece with the base plate of the combustion chamber or are fixed or movably fastened thereon. In the US 5,524,438 A In a further variation, this anti-rotation device is represented by a sheet metal ring with radial tabs which engage in recesses in adjacent ring-shaped components. These radial tabs are not used as elastic elements during assembly.

Bei den aus dem Stand der Technik bekannten Lösungen ergeben sich folgende Nachteile:
Die in der DE 44 27 222 A1 verwendeten Abstandsscheiben werden an die Maße der Vertiefung angepasst, was die Montage verlangsamt. Die in der DE 100 48 864 A1 vorgeschlagenen Halterungen positionieren zwei Dichtungen, so dass beim Ansetzen der Muttern auf die Bolzen der Hitzeschilder drei Bauteile festgehalten werden müssen, was die Montage ebenfalls schwierig gestaltet. Der in der US 5,419,115 A und der US 5,463,864 A vorgesehene Fügeprozess im beengten Bauraum des Brennkammerkopfes stellt einen schwierig auszuführenden Prozessschritt mit einem schwierig zu prüfenden Ergebnis dar. Insgesamt erscheinen alle vorgeschlagenen Lösungen durch die vielen zu fertigenden und zu fügenden Bauteile kompliziert, teuer und schwer.The solutions known from the prior art have the following disadvantages:
The in the DE 44 27 222 A1 used spacers are adapted to the dimensions of the recess, which slows down the assembly. The in the DE 100 48 864 A1 Proposed brackets position two seals, so that three components must be held when the nuts are placed on the bolts of the heat shields, which also makes assembly difficult. The Indian US 5,419,115 A and the US 5,463,864 A The proposed joining process in the cramped installation space of the combustion chamber head represents a difficult process step with a result that is difficult to test. All proposed appear overall Solutions due to the many components to be manufactured and joined complicated, expensive and difficult.

Ferner zeigt US 5 222 358 A ein System zur wieder lösbaren Montage eines Vorverdampfertopfes an einer Brennkammer eines Gasturbinentriebwerks.Furthermore shows US 5 222 358 A a system for the releasable mounting of a pre-evaporator pot on a combustion chamber of a gas turbine engine.

Aus EP 1 193 451 A2 ist ein Brennkammerkopf einer Gasturbine mit einem Hitzeschild und einer Manschette, welche mit Halteelementen in Position gehalten wird, bekannt.Out EP 1 193 451 A2 a combustor head of a gas turbine with a heat shield and a sleeve, which is held in position with holding elements, is known.

WO 96/18853 A1 zeigt eine Halterung einer Kraftstoffdüse eines Gasturbinenbrenners. WO 96/18853 A1 shows a holder of a fuel nozzle of a gas turbine burner.

Weiterhin zeigt US 2006/042269 A1 eine Gasturbinen-Kraftstoffdüse, welche mittels einer gleitenden Manschette gehalten wird.Furthermore shows US 2006/042269 A1 a gas turbine fuel nozzle, which is held by means of a sliding sleeve.

Der Erfindung liegt die Aufgabe zugrunde, einen Brennkammerkopf der eingangs genannten Art zu schaffen, welcher bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit eine einfache Ausgestaltung der Brennerdichtung aufweist und einfach und kostengünstig montierbar ist.The invention has for its object to provide a combustion chamber head of the type mentioned, which has a simple design and simple, inexpensive to manufacture, a simple design of the burner seal and is simple and inexpensive to assemble.

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 subclaims show further advantageous refinements of the invention.

Erfindungsgemäß ist somit vorgesehen, dass der Brennkammerkopf eine Grundplatte aufweist, welche mit einer zentrischen Ausnehmung versehen ist, in welcher zumindest ein Brenner angeordnet ist. Die Grundplatte ist an ihren radial inneren und äußeren Bereichen mit Wandungen der Brennkammer, insbesondere einer inneren und einer äußeren Wandung einer Ringbrennkammer (Brennkammergehäuse), verbunden. Weiterhin ist erfindungsgemäß eine den Brenner zum Rand der Ausnehmung abdichtende Brennerdichtung vorgesehen. Die Brennerdichtung ist erfindungsgemäß stromauf der Grundplatte angeordnet und gegen einen an der Grundplatte ausgebildeten, den Rand der zentrischen Ausnehmung bildenden Kragen zur Anlage bringbar. Hierdurch erfolgt eine Abdichtung der Brennerdichtung gegenüber der Grundplatte. Weiterhin ist erfindungsgemäß vorgesehen, dass ein Halteelement der Brennerdichtung in Form eines Rings ausgebildet ist und stromauf der Brennerdichtung angeordnet ist. Das ringförmige Halteelement ist mit zumindest einem Ansatz der Grundplatte in Eingriff. Dieser Ansatz kann beispielsweise in Form einer Aufdickung ausgebildet sein.It is therefore provided according to the invention that the combustion chamber head has a base plate which is provided with a central recess in which at least one burner is arranged. The base plate is connected at its radially inner and outer areas to walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing). Furthermore, a burner seal sealing the burner to the edge of the recess is provided according to the invention. According to the invention, the burner seal is arranged upstream of the base plate and can be brought into abutment against a collar formed on the base plate and forming the edge of the central recess. This creates a seal between the burner seal and the base plate. Furthermore, it is provided according to the invention that a holding element of the burner seal is designed in the form of a ring and is arranged upstream of the burner seal. The annular holding element is in engagement with at least one shoulder of the base plate. This approach can be designed, for example, in the form of a thickening.

Weiterhin ist vorgesehen, dass das ringförmige Halteelement mit zumindest einer Verriegelungslasche versehen ist, welche mit dem Ansatz der Grundplatte (Aufdickung) in Eingriff ist. Die Lasche ist bevorzugterweise am Innenring des ringförmigen Halteelements angeordnet, erfindungsgemäß ist es auch möglich, die Lasche am Außenring des ringförmigen Halteelements auszubilden.Furthermore, it is provided that the ring-shaped holding element is provided with at least one locking tab which engages with the attachment of the base plate (thickening). The tab is preferably arranged on the inner ring of the annular holding element; according to the invention it is also possible to form the tab on the outer ring of the annular holding element.

Um die Lasche in Eingriff mit dem Ansatz zu bringen, weist dieser eine Ausnehmung auf, in welche die Lasche einbringbar ist, insbesondere durch Verformung der Lasche.In order to bring the tab into engagement with the extension, it has a recess into which the tab can be inserted, in particular by deforming the tab.

Um die Montage des Brenners zu erleichtern, ist die Brennerdichtung an ihrer stromauf liegenden Seite trichterförmig ausgebildet.In order to facilitate the assembly of the burner, the burner seal is funnel-shaped on its upstream side.

Erfindungsgemäß ist somit vorgesehen, die Dichtung, wie in DE 100 48 864 A1 stromauf der Grundplatte der Brennkammer vorzusehen, wobei diese auf einem um die Ausnehmung zur Durchführung der Brennerdichtung umlaufenden Kragen der Grundplatte zur Anlage bringbar ist wobei eine Halterung der Brennerdichtung ein einfacher Blechring mit zum Beispiel drei nach außen stehenden Laschen ist, welche in Ausnehmungen in Aufdickungen der Grundplatte der Brennkammer eingreifen. Zugleich hat die Brennerdichtung am stromauf liegenden Ende einen Zuführtrichter, der die Montage des Brenners erleichtert und im Betrieb keine weitere Funktion mehr erfüllt.According to the invention it is thus provided that the seal, as in DE 100 48 864 A1 to be provided upstream of the base plate of the combustion chamber, which can be brought to bear on a collar of the base plate which runs around the recess for carrying out the burner seal, and a holder for the burner seal is a simple sheet metal ring with, for example, three outwardly projecting tabs, which are formed in recesses in thickened areas Engage the base plate of the combustion chamber. At the same time, the burner seal has a feed funnel at the upstream end, which simplifies the assembly of the burner and no longer fulfills any other function during operation.

Drei Ansätze der Aufdickungen der Grundplatte dienen während der mechanischen Bearbeitung des Brennkammerkopfes als permanente Referenz. Die Laschen an der ringförmigen Dichtungshalterung können am Innen- oder Außenrand der Dichtungshalterung angebracht sein.Three approaches to the thickening of the base plate serve as a permanent reference during the mechanical processing of the combustion chamber head. The tabs on the annular seal holder can be attached to the inner or outer edge of the seal holder.

Zur Montage wird das ringförmige Halteelement (Blechring) so über die Brennerdichtung gelegt, dass die Laschen neben den Ausnehmungen in den drei Ausnehmungen der Aufdickungen der Grundplatte zu liegen kommen. Dann werden die Laschen des ringförmigen Halteelements durch ein entsprechend geformtes Werkzeug in Richtung Grundplatte gedrückt und das ringförmige Halteelement um einen kleinen Winkelbetrag verdreht. Dadurch greifen die Laschen so in die Ausnehmungen der Aufdickung (des Ansatzes) der Grundplatte ein, dass sich das ringförmige Halteelement nicht mehr zurückdrehen kann, die Laschen aber in ihre ursprüngliche Form zurückspringen können ohne weiterhin unter Spannung zu stehen. Eine Verdrehsicherung für die Brennerdichtung selbst ist nach allgemeiner Betriebserfahrung nicht notwendig und wird daher durch die hier aufgeschlagene Montage auch nicht ermöglicht.For assembly, the ring-shaped holding element (sheet metal ring) is placed over the burner seal in such a way that the tabs come to rest next to the recesses in the three recesses of the thickened base plate. Then the tabs of the ring-shaped holding element are pressed in the direction of the base plate by a correspondingly shaped tool and the ring-shaped holding element is rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the attachment) of the base plate in such a way that the annular holding element can no longer turn back, but the tabs can spring back into their original shape without being under tension. An anti-twist device for the burner seal itself is not necessary according to general operating experience and is therefore not made possible by the installation described here.

In der Herstellung der Brennkammer und auch später bei der Reparatur von beschädigten Brennkammern stehen dieselben Bezugspunkte in Form von Ansätzen von Aufdickungen für eine mechanische Bearbeitung der Brennkammer zur Verfügung. Zwischen Herstellung und Überholung der Brennkammer erfüllen diese Ansätze von Aufdickungen die Funktion einer Dichtungshalterung. Während der Montage wird die Brennerdichtung durch ein Werkzeug zentriert. Die Halterung der Brennerdichtung wird ebenfalls durch das Werkzeug zentriert und bewegt. Dadurch muss der Monteur nur ein Werkzeug anfassen und nicht drei Teile gleichzeitig. Hierdurch wird die Montage sicher und schnell ausgeführt und es sind keinerlei Fügeprozesse notwendig. Dies ermöglicht eine präzise, wiederholbare und leichte und kostengünstige Montage. Durch den spannungslosen Zustand der Halterung im eingerasteten Zustand kommt es in dieser auch zu keinen Ermüdungserscheinungen im Betrieb des Triebwerks. Während der gesamten Betriebsdauer der Brennerdichtung wird diese nahe am Brennkammerkopf gehalten. Die Dichtkraft wird durch die Druckdifferenz zwischen der die Brennkammer umströmenden Luft und der Luft in der Brennkammer und nicht durch die Halterung der Brennerdichtung erzeugt. Durch den integrierten Zuführtrichter wird kein zusätzliches Bauteil für diese Funktion benötigt, welches wiederum zuverlässig und betriebssicher befestigt werden müsste. Die Kosten für die Herstellung und Montage einer Verdrehsicherung werden eingespart, da diese Funktion nicht notwendig ist.In the manufacture of the combustion chamber and also later in the repair of damaged combustion chambers, the same reference points are available in the form of approaches of thickening for mechanical processing of the combustion chamber. Between manufacture and overhaul of the combustion chamber, these approaches of thickening serve the function of a seal holder. The torch seal is centered using a tool during assembly. The holder of the burner seal is also centered and moved by the tool. This means that the fitter only has to touch one tool and not three parts at the same time. As a result, the assembly is carried out safely and quickly and no joining processes are necessary. This enables precise, repeatable and easy and inexpensive assembly. Due to the de-energized state of the holder in the locked state, there are also no signs of fatigue during operation of the engine. The burner seal is kept close to the combustion chamber head during the entire operating time. The sealing force is generated by the pressure difference between the air flowing around the combustion chamber and the air in the combustion chamber and not by the holder of the burner seal. Thanks to the integrated feed hopper, no additional component is required for this function, which in turn would have to be attached reliably and reliably. The costs for the manufacture and assembly of an anti-rotation device are saved since this function is not necessary.

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 schematische vergrößerte Detailansicht einer erfindungsgemäßen Brennkammer mit zugehörigen Bauelementen der Gasturbine,
Fig. 3
eine vergrößerte Detail-Schnittansicht in schematischer Darstellung eines Ausführungsbeispiels der erfindungsgemäßen Lösung,
Fig. 4
eine perspektivische Teilansicht der Grundplatte mit Kragen,
Fig. 5
eine vereinfachte Teil-Seitenansicht der Frontplatte mit Kragen und Ansatz,
Fig. 6
eine Darstellung analog Fig. 5 im montierten Zustand der Brennerdichtung und deren Halterung,
Fig. 7
eine Darstellung, analog den Fig. 5 und 6, eines weiteren Ausführungsbeispiels mit montierter Brennerdichtung und Halterung, und
Fig. 8
vereinfachte Darstellungen von Ausführungsbeispielen der erfindungsgemäßen Halterung.
The invention is described below on the basis of exemplary embodiments in conjunction with the drawing. It shows:
Fig. 1
1 shows a schematic illustration of a gas turbine engine according to the present invention,
Fig. 2
2 shows a schematic enlarged detailed view of a combustion chamber according to the invention with associated components of the gas turbine,
Fig. 3
2 shows an enlarged detail sectional view in a schematic representation of an exemplary embodiment of the solution according to the invention,
Fig. 4
a partial perspective view of the base plate with collar,
Fig. 5
a simplified partial side view of the front panel with collar and neck,
Fig. 6
a representation analog Fig. 5 in the assembled state of the burner seal and its holder,
Fig. 7
a representation, analogous to the 5 and 6 , a further embodiment with the burner seal and holder fitted, and
Fig. 8
Simplified representations of exemplary embodiments of the holder according to the invention.

Das Gasturbinentriebwerk 10 gemäß Fig. 1 ist ein Beispiel einer Turbomaschine, bei der die Erfindung Anwendung finden kann. Aus dem Folgenden wird jedoch klar, dass die Erfindung auch bei anderen Turbomaschinen verwendet werden kann. Das Triebwerk 10 ist in herkömmlicher Weise ausgebildet und umfasst in Strömungsrichtung hintereinander einen Lufteinlass 11, einen in einem Gehäuse umlaufenden Fan 12, einen Zwischendruckkompressor 13, einen Hochdruckkompressor 14, Brennkammern 15, eine Hochdruckturbine 16, eine Zwischendruckturbine 17 und eine Niederdruckturbine 18 sowie eine Abgasdüse 19, die sämtlich um eine zentrale Triebwerksachse 1 angeordnet sind.The gas turbine engine 10 according to Fig. 1 is an example of a turbomachine to which the invention can be applied. However, it is clear from the following that the invention can also be used in other turbomachinery. The engine 10 is designed in a conventional manner and comprises an air inlet 11, a fan 12 rotating in a housing, an intermediate pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18 and an exhaust gas nozzle in the flow direction 19, which are all arranged around a central engine axis 1.

Der Zwischendruckkompressor 13 und der Hochdruckkompressor 14 umfassen jeweils mehrere Stufen, von denen jede eine in Umfangsrichtung verlaufende Anordnung fester stationärer Leitschaufeln 20 aufweist, die allgemein als Statorschaufeln bezeichnet werden und die radial nach innen vom Triebwerksgehäuse 21 in einem ringförmigen Strömungskanal durch die Kompressoren 13, 14 vorstehen. Die Kompressoren weisen weiter eine Anordnung von Kompressorlaufschaufeln 22 auf, die radial nach außen von einer drehbaren Trommel oder Scheibe 26 vorstehen, die mit Naben 27 der Hochdruckturbine 16 bzw. der Zwischendruckturbine 17 gekoppelt sind.The intermediate pressure compressor 13 and the high pressure compressor 14 each comprise a plurality of stages, each of which has a circumferential arrangement of fixed stationary guide vanes 20, which are generally referred to as stator vanes, and which extend radially inward from the engine housing 21 in an annular flow channel through the compressors 13, 14 protrude. The compressors also have an arrangement of compressor blades 22 which protrude radially outward from a rotatable drum or disk 26 which are coupled to hubs 27 of the high-pressure turbine 16 or the intermediate-pressure turbine 17.

Die Turbinenabschnitte 16, 17, 18 weisen ähnliche Stufen auf, umfassend eine Anordnung von festen Leitschaufeln 23, die radial nach innen vom Gehäuse 21 in den ringförmigen Strömungskanal durch die Turbinen 16, 17, 18 vorstehen, und eine nachfolgende Anordnung von Turbinenschaufeln 24, die nach außen von einer drehbaren Nabe 27 vorstehen. Die Kompressortrommel oder Kompressorscheibe 26 und die darauf angeordneten Schaufeln 22 sowie die Turbinenrotornabe 27 und die darauf angeordneten Turbinenlaufschaufeln 24 drehen sich im Betrieb um die Triebwerksachse 1.The turbine sections 16, 17, 18 have similar steps, comprising an arrangement of fixed guide vanes 23 which extend radially inward from the housing 21 into the annular flow channel project through the turbines 16, 17, 18, and a subsequent array of turbine blades 24 projecting outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the blades 22 arranged thereon and the turbine rotor hub 27 and the turbine rotor blades 24 arranged thereon rotate during operation about the engine axis 1.

Die Fig. 2 zeigt in vereinfachter schematischer Darstellung den Bereich einer Brennkammer 108 einer Gasturbine. Diese umfasst ein inneres Brennkammergehäuse 109 sowie ein äußeres Brennkammergehäuse 110. Stromauf der Brennkammer 108 ist ein Brennkammerkopf 107 angeordnet, in welchem ein Brenner 106 mit Arm und Kopf angeordnet ist. Die Luftzuführung zu der Brennkammer 8 erfolgt über ein Frontgebläse 101 (Fan), welcher von einer Antriebswelle 102 angetrieben wird. Mit der Antriebswelle 102 ist auch ein Verdichter 103 verbunden. Das Bezugszeichen 104 zeigt einen Nebenstrom (Nebenstromkanal). Die anströmende Luft wird über ein Verdichteraustrittsleitrad 105 mit Diffuser geleitet. Die aus der Brennkammer 108 austretende Strömung wird durch ein Turbinenleitrad 111 sowie ein Turbinenlaufrad 112 durchgeführt.The Fig. 2 shows the area of a combustion chamber 108 of a gas turbine in a simplified schematic representation. This includes an inner combustion chamber housing 109 and an outer combustion chamber housing 110. A combustion chamber head 107 is arranged upstream of the combustion chamber 108, in which a burner 106 with arm and head is arranged. The air supply to the combustion chamber 8 takes place via a front fan 101 (fan) which is driven by a drive shaft 102. A compressor 103 is also connected to the drive shaft 102. Reference numeral 104 shows a bypass flow (bypass flow channel). The incoming air is directed via a compressor outlet stator 105 with a diffuser. The flow emerging from the combustion chamber 108 is carried out by a turbine stator 111 and a turbine impeller 112.

Die Fig. 3 zeigt in schematischer Detailansicht ein Ausführungsbeispiel der erfindungsgemäßen Lösung. Erfindungsgemäß ist am stromauf liegenden Endbereich der Brennkammer 108 eine Grundplatte 113 angeordnet, welche mit einer Ausnehmung versehen ist, welche durch einen Kragen 118 begrenzt wird. Durch die Ausnehmung wird der Brenner 106 durchgeführt, so wie dies in den Fig. 1 und 2 dargestellt ist. Die Grundplatte 113 ist mit einem Ansatz 114 (Aufdickung) versehen. Die Aufdickung 114 lagert in einer Ausnehmung 115 eine Brennerdichtung 116, welche ringförmig ausgebildet ist, so wie dies aus dem Stand der Technik bekannt ist. Die Brennerdichtung 116 wird über ein Halteelement 117 (Haltering) gehalten, so wie dies in den nachfolgenden Figuren beschrieben wird.The Fig. 3 shows a schematic detailed view of an embodiment of the solution according to the invention. According to the invention, a base plate 113 is arranged on the upstream end region of the combustion chamber 108 and is provided with a recess which is delimited by a collar 118. The burner 106 is passed through the recess, as shown in FIGS Fig. 1 and 2 is shown. The base plate 113 is provided with an extension 114 (thickening). The thickening 114 supports a burner seal 116 in a recess 115, which is ring-shaped, as is known from the prior art. The burner seal 116 is held by a holding element 117 (holding ring), as is described in the following figures.

Die Fig. 4 zeigt einen Teil der kreisringförmig ausgebildeten Grundplatte 113, welche mit dem Kragen 118 versehen ist, der die Ausnehmung 121 zur Durchführung des Brenners 106 begrenzt. Um den Umfang des Kragens 118 verteilt sind drei Ansätze 114 (Aufdickungen der Grundplatte 113) vorgesehen.The Fig. 4 shows a part of the annular base plate 113, which is provided with the collar 118, which delimits the recess 121 for the passage of the burner 106. Distributed around the circumference of the collar 118 are three lugs 114 (thickening of the base plate 113).

Die Fig. 5 zeigt eine schematisierte Teil-Seitenschnittansicht der Grundplatte 113 mit dem Kragen 118 und einem Ansatz 114 mit einer Ausnehmung 115. Die Fig. 6 zeigt die in Fig. 5 dargestellte Anordnung im montierten Zustand der ringförmigen Brennerdichtung 116 sowie des Halteelements 117 (Haltering). Das Halteelement 117 zeigt eine Verriegelungslasche (Lasche) 120, so wie dies nachfolgend noch beschrieben werden wird. Die Fig. 6 zeigt dabei die Anordnung der Verriegelungslasche 120 am radial äußeren Bereich des Halterings 117, so wie dies in der rechten Bildhälfte der Fig. 8 dargestellt ist. Dort sind am Umfang verteilt drei Verriegelungslaschen (Laschen) 120 dargestellt.The Fig. 5 shows a schematic partial side sectional view of the base plate 113 with the collar 118 and an approach 114 with a recess 115. Die Fig. 6 shows the in Fig. 5 Arrangement shown in the assembled state of the annular burner seal 116 and the holding element 117 (retaining ring). The holding element 117 shows a locking tab (tab) 120, as will be described below. The Fig. 6 shows the arrangement of the locking tab 120 on the radially outer region of the retaining ring 117, as shown in the right half of the figure Fig. 8 is shown. There are three locking tabs (tabs) 120 distributed around the circumference.

Die Fig. 7 zeigt eine Variante, bei welcher die Verriegelungslasche 120 in die Ausnehmung 115 des Ansatzes 114 eingebracht ist. Es ist somit der fertig montierte Zustand dargestellt.The Fig. 7 shows a variant in which the locking tab 120 is introduced into the recess 115 of the extension 114. The fully assembled state is thus shown.

Die rechte Bildhälfte der Fig. 8 zeigt Varianten der Verriegelungslaschen, nämlich eine Verriegelungslasche 120a des Dichtungshalters (Haltering 117). Die Variante der Verriegelungslasche 120b ist außen an dem Haltering 117 angeordnet, während die Variante der Verriegelungslasche 120c innen am Haltering 117 angeordnet ist. Die Verriegelungslaschen 120b und 120c sind jeweils im gebogenen Zustand dargestellt.The right half of the picture Fig. 8 shows variants of the locking tabs, namely a locking tab 120a of the seal holder (retaining ring 117). The variant of the locking tab 120b is arranged on the outside of the holding ring 117, while the variant of the locking tab 120c is arranged on the inside of the holding ring 117. The locking tabs 120b and 120c are each shown in the bent state.

Bezugszeichenliste:Reference symbol list:

11
TriebwerksachseEngine axis
1010
GasturbinentriebwerkGas turbine engine
1111
LufteinlassAir intake
1212th
im Gehäuse umlaufender Fanfan in the casing
1313
ZwischendruckkompressorIntermediate pressure compressor
1414
HochdruckkompressorHigh pressure compressor
1515
BrennkammernCombustion chambers
1616
HochdruckturbineHigh pressure turbine
1717
ZwischendruckturbineIntermediate pressure turbine
1818th
NiederdruckturbineLow pressure turbine
1919
AbgasdüseExhaust nozzle
2020th
LeitschaufelnGuide vanes
2121
TriebwerksgehäuseEngine housing
2222
KompressorlaufschaufelnCompressor blades
2323
LeitschaufelnGuide vanes
2424
TurbinenschaufelnTurbine blades
2626
Kompressortrommel oder -scheibeCompressor drum or disk
2727
TurbinenrotornabeTurbine rotor hub
2828
AbgaskonusExhaust cone
101101
Frontgebläse (Fan)Front fan (fan)
102102
Antriebswelledrive shaft
103103
Verdichtercompressor
104104
NebenstromSidestream
105105
Verdichteraustrittsleitrad mit DiffuserCompressor outlet guide wheel with diffuser
106106
Brenner mit Arm und KopfBurner with arm and head
107107
BrennkammerkopfCombustion chamber head
108108
BrennkammerCombustion chamber
109109
Inneres BrennkammergehäuseInner combustion chamber housing
110110
Äußeres BrennkammergehäuseExternal combustion chamber housing
111111
TurbinenleitradTurbine idler
112112
TurbinenlaufradTurbine impeller
113113
Grundplatte der Brennkammer 108Base plate of the combustion chamber 108
114114
Aufdickung der Grundplatte 113 / AnsatzThickening of the base plate 113 / approach
115115
Ausnehmung der Aufdickung 114Recess of the thickening 114
116116
BrennerdichtungBurner seal
117117
Halterung der Brennerdichtung / Halteelement / HalteringBracket seal holder / retaining element / retaining ring
118118
Kragen der Grundplatte 113 zur Auflage der Brennerdichtung 116Collar of the base plate 113 for supporting the burner seal 116
119119
Abdeckung der Grundplatte 113Covering the base plate 113
120a120a
Verriegelungslasche des Dichtungshalters 117Locking tab of the seal holder 117
120b120b
gebogene Variante der Verriegelungslasche, außen am Dichtungshalter 117curved version of the locking tab, on the outside of the seal holder 117
120c120c
gebogene Variante der Verriegelungslasche, innen am Dichtungshalter 117curved version of the locking tab, inside on the seal holder 117
121121
AusnehmungRecess

Claims (3)

  1. Combustion chamber head of a gas turbine having a base plate (113) which is provided with a central recess (121), in which at least one burner (106) is arranged, wherein the base plate (113) is connected to walls of the combustion chamber (108), and having a burner seal (116) sealing off the burner (106) relative to the edge of the recess (121), wherein the burner seal (116) is arranged upstream of the base plate (113) and can be brought into contact against a collar (118) formed on the base plate (113) and forming the edge of the central recess (121), and wherein a holding element (117) of the burner seal (116) is formed in the shape of a sheet metal ring and is arranged upstream of the burner seal (116) and is in tension-free engagement with at least one projection (114) of the base plate (113), characterized in that the holding element (117) is provided with at least one locking tab (120a, 120b, 120c), which is in tension-free engagement with the projection (114),
    wherein the projection (114) is provided with at least one recess (115) for the engagement of the locking tab (120a, 120b, 120c), and
    wherein the burner seal (113) is formed in the shape of a funnel on its upstream side for the insertion of the burner (106).
  2. Combustion chamber head according to Claim 1, characterized in that the tab (120a, 120b, 120c) is arranged on the inner edge of the annular holding element (117).
  3. Combustion chamber head according to Claim 1, characterized in that the tab (120a, 120b, 120c) is arranged on the outer edge of the annular holding element (117).
EP12002047.4A 2011-03-24 2012-03-22 Combustion chamber head with holder for burner seals in gas turbines Active EP2503242B1 (en)

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GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
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US9222675B2 (en) 2015-12-29
EP2503242A2 (en) 2012-09-26
EP2503242A3 (en) 2017-11-08
DE102011014972A1 (en) 2012-09-27
US20120240595A1 (en) 2012-09-27

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