EP2503242A2 - 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
EP2503242A2
EP2503242A2 EP12002047A EP12002047A EP2503242A2 EP 2503242 A2 EP2503242 A2 EP 2503242A2 EP 12002047 A EP12002047 A EP 12002047A EP 12002047 A EP12002047 A EP 12002047A EP 2503242 A2 EP2503242 A2 EP 2503242A2
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EP
European Patent Office
Prior art keywords
burner
combustion chamber
seal
base plate
recess
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12002047A
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German (de)
French (fr)
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EP2503242A3 (en
EP2503242B1 (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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Publication of EP2503242A2 publication Critical patent/EP2503242A2/en
Publication of EP2503242A3 publication Critical patent/EP2503242A3/en
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Publication of EP2503242B1 publication Critical patent/EP2503242B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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 detail, the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • a gasket around a burner of a gas turbine is shown disposed upstream of a base plate of the combustor, projecting through it and a heat shield into the combustion chamber and performing the same function as described above.
  • the seal can not leave their intended place, but only be moved along the burner in the axial direction.
  • the actual sealing force which is absolutely necessary for the generation and maintenance of the sealing function, is usually not provided by gas turbine combustors 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.
  • a device which is the seal Positioned near the sealing surface without pressing it.
  • the axial positioning is adjusted by a spacer disc, which is located between the base plate of the combustion chamber and the seal.
  • the radial positioning of the seal prior to installation of the Burner is ensured by the shape of the recess in the base plate of the combustion chamber.
  • 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.
  • the in the DE 44 27 222 A1 used shims are adapted to the dimensions of the recess, which slows down the assembly.
  • the in the DE 100 48 864 A1 proposed mounts position two seals, so that when attaching the nuts on the bolts of the heat shields three components must be held, which also makes the assembly difficult.
  • the Indian US 5,419,115 A and the US 5,463,864 A provided joining process in the confined space of the combustion chamber head is a difficult to perform process step with a difficult-to-test result. Overall, all proposed Solutions through the many components to be manufactured and joined complicated, expensive and difficult.
  • the invention has for its object to provide a combustion chamber head of the type mentioned, which has a simple design and simple, cost-effective manufacturability a simple design of the burner seal and is easy and inexpensive to install.
  • 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 regions with walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing).
  • a burner sealing the burner to the edge of the recess is provided.
  • the burner seal according to the invention arranged upstream of the base plate and against a formed on the base plate, the edge of the central recess forming collar for conditioning brought. This seals the burner seal against the base plate.
  • the invention provides 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 retaining element is engaged with at least one shoulder of the base plate. This approach can be designed for example in the form of a thickening.
  • the annular holding element is provided with at least one locking tab, which is in engagement with the attachment of the base plate (thickening).
  • the tab is preferably arranged on the inner ring of the annular retaining element, according to the invention it is also possible to form the tab on the outer ring of the annular retaining element.
  • this preferably has a recess into which the tab can be introduced, in particular by deformation of the tab.
  • the burner seal is funnel-shaped on its upstream side.
  • the seal as in DE 100 48 864 A1 Provide upstream of the base plate of the combustion chamber, which can be brought to bear on a recess for carrying out the burner seal collar of the base plate to the plant a holder of the burner seal is a simple sheet metal ring with, for example, three outward tabs, which in recesses in the thickenings of Engage the base plate of the combustion chamber.
  • the burner seal at the upstream end has a feed funnel, which facilitates the assembly of the burner and fulfills no further function during operation.
  • the tabs on the annular seal retainer may be attached to the inner or outer edge of the seal retainer.
  • the annular holding element (sheet metal ring) is placed over the burner seal, that the tabs come to rest next to the recesses in the three recesses of the thicker portions of the base plate. Then the tabs of the annular support member are pressed by a correspondingly shaped tool in the direction of the base plate and the annular support member rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the approach) of the base plate so that the annular retaining element can not turn back, but the tabs can spring back to their original shape without being under tension.
  • An anti-rotation device for the burner seal itself is not necessary for general operating experience and is therefore not made possible by the here pitched assembly.
  • the integrated feed hopper eliminates the need for an additional component for this function, which in turn would need to be reliably and operationally secured. The costs for the production and installation of an anti-rotation device are saved as this function is not necessary.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating 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 nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar steps, comprising an array of fixed vanes 23 extending radially inward from the housing 21 into the housing annular flow channel through the turbines 16, 17, 18 protrude, and a subsequent arrangement of turbine blades 24 which project outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows in a simplified schematic representation of the area of a combustion chamber 108 of a gas turbine.
  • This comprises an inner combustion chamber housing 109 and an outer combustion chamber housing 110.
  • a combustion chamber head 107 is arranged, in which a burner 106 with arm and head is arranged.
  • a compressor 103 is also connected to the drive shaft 102.
  • the reference numeral 104 shows a side stream (bypass channel).
  • the incoming air is passed through a compressor outlet guide 105 with diffuser.
  • the flow exiting the combustion chamber 108 is performed by a turbine nozzle 111 and a turbine runner 112.
  • the Fig. 3 shows a schematic detail view of an embodiment of the inventive solution.
  • a base plate 113 is arranged at the upstream end region of the combustion chamber 108, which is provided with a recess which is delimited by a collar 118. Through the recess of the burner 106 is performed, as in the Fig. 1 and 2 is shown.
  • the base plate 113 is provided with a projection 114 (thickening).
  • the thickening 114 supports in a recess 115 a burner seal 116, which is annular, as known from the prior art.
  • the burner seal 116 is held by a retaining element 117 (retaining ring), as described in the following figures.
  • the Fig. 4 shows a portion of the annular base plate 113, which is provided with the collar 118 which limits the recess 121 for the passage of the burner 106.
  • Distributed around the circumference of the collar 118 are three lugs 114 (thickenings 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 a projection 114 with a recess 115.
  • Die Fig. 6 shows the in Fig. 5 shown arrangement in the mounted state of the annular burner seal 116 and the retaining 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 at the radially outer region of the retaining ring 117, as in the right half of the Fig. 8 is shown. There are three circumferentially distributed locking tabs (tabs) 120 shown.
  • the Fig. 7 shows a variant in which the locking tab 120 is inserted into the recess 115 of the projection 114. It is thus shown the finished assembled state.
  • 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 retaining ring 117, while the variant of the locking tab 120c is arranged on the inside of the retaining ring 117.
  • the locking tabs 120b and 120c are each shown in the bent state.

Abstract

The head has a base plate (113) provided with a centric recess in which a burner is arranged. The plate is connected to walls of the combustion chamber and with a burner seal (116) that seals the burner towards a rim of the recess. The burner seal is arranged upstream of the plate and brought into contact with a collar (118). The collar is provided on the plate, and forms the rim of the recess. The seal has a holding element (117) that is formed as a sheet ring and arranged upstream of the seal, where the element is engaged with a projection (114) of the plate in a tension-free 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 detail, 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 For example, a seal about a combustor of a gas turbine disposed downstream of a base plate of the combustion chamber, protrudes through a heat shield into the combustion chamber and compensates for the movement between the burner mounted in the combustion chamber housing and the combustion chamber itself is unacceptable Leaks arise. In the narrower sense gas-tight, this type of seal does not need to be.

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 For example, a gasket around a burner of a gas turbine is shown disposed upstream of a base plate of the combustor, projecting through it and a heat shield into the combustion chamber and performing 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.Once the burner is used, the seal can not leave their intended place, but only be moved along the burner in the axial direction. The actual sealing force, which is absolutely necessary for the generation and maintenance of the sealing function, is usually not provided by gas turbine combustors 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.However, before the burner is used and to ensure that the gasket is close to the sealing surface when starting the gas turbine and then actually pressed by the resulting pressure difference to the base plate of the combustion chamber or the heat shield, a device must be provided, which is the seal Positioned near the sealing surface without pressing it. At the time of the DE 44 27 222 A1 known solution, the axial positioning is adjusted by a spacer disc, which is located between the base plate of the combustion chamber and the seal. The radial positioning of the seal prior to installation of the Burner is ensured by the shape of the recess in the base plate of the combustion chamber. At the time of 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.Another solution show the US 5,419,115 A and the US 5,463,864 A , Here, the guide and seal of the burner is mounted only after the heat shield from the downstream side of the combustion chamber head and then attached upstream of the head by a one or two piece holder attached to this burner guide. This is done so that this device of leadership and support can still perform small sliding movements in the radial and lateral directions, in turn, to allow the insertion of the burner and balanced in operation, the relative movements between the combustion chamber housing in which the burner is mounted, and the combustion chamber can be. In both publications, different embodiments of an anti-rotation for the leadership of the burner and its seal are shown, which are designed in part integrally with the base plate of the combustion chamber or fixed or movably mounted on this. In the US 5,524,438 A is shown in a further variation of this rotation by a sheet metal ring with radial tabs, which engage in recesses of adjacent annular components. These radial tabs are not used during assembly as elastic elements.

Bei den aus dem Stand der Technik bekannten Lösungen ergeben sich folgende Nachteile:The solutions known from the prior art have the following disadvantages:

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 in the DE 44 27 222 A1 used shims are adapted to the dimensions of the recess, which slows down the assembly. The in the DE 100 48 864 A1 proposed mounts position two seals, so that when attaching the nuts on the bolts of the heat shields three components must be held, which also makes the assembly difficult. The Indian US 5,419,115 A and the US 5,463,864 A provided joining process in the confined space of the combustion chamber head is a difficult to perform process step with a difficult-to-test result. Overall, all proposed Solutions through the many components to be manufactured and joined complicated, expensive and difficult.

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, cost-effective manufacturability a simple design of the burner seal and is easy and inexpensive to install.

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 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.According to the invention it is thus provided 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 regions with walls of the combustion chamber, in particular an inner and an outer wall of an annular combustion chamber (combustion chamber housing). Furthermore, according to the invention, a burner sealing the burner to the edge of the recess is provided. The burner seal according to the invention arranged upstream of the base plate and against a formed on the base plate, the edge of the central recess forming collar for conditioning brought. This seals the burner seal against the base plate. Furthermore, the invention provides 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 retaining element is engaged with at least one shoulder of the base plate. This approach can be designed for example in the form of a thickening.

In günstiger Weiterbildung der Erfindung 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.In a favorable development of the invention, it is provided that the annular holding element is provided with at least one locking tab, which is in engagement with the attachment of the base plate (thickening). The tab is preferably arranged on the inner ring of the annular retaining element, according to the invention it is also possible to form the tab on the outer ring of the annular retaining element.

Um die Lasche in Eingriff mit dem Ansatz zu bringen, weist dieser bevorzugterweise eine Ausnehmung auf, in welche die Lasche einbringbar ist, insbesondere durch Verformung der Lasche.In order to bring the tab into engagement with the approach, this preferably has a recess into which the tab can be introduced, in particular by deformation of the tab.

Um die Montage des Brenners zu erleichtern, ist es besonders günstig, wenn die Brennerdichtung an ihrer stromauf liegenden Seite trichterförmig ausgebildet ist.In order to facilitate the assembly of the burner, it is particularly advantageous if 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 is thus provided, the seal, as in DE 100 48 864 A1 Provide upstream of the base plate of the combustion chamber, which can be brought to bear on a recess for carrying out the burner seal collar of the base plate to the plant a holder of the burner seal is a simple sheet metal ring with, for example, three outward tabs, which in recesses in the thickenings of Engage the base plate of the combustion chamber. At the same time, the burner seal at the upstream end has a feed funnel, which facilitates the assembly of the burner and fulfills no further 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 base plate thickening serve as a permanent reference during mechanical machining of the combustion head. The tabs on the annular seal retainer may be attached to the inner or outer edge of the seal retainer.

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 mounting, the annular holding element (sheet metal ring) is placed over the burner seal, that the tabs come to rest next to the recesses in the three recesses of the thicker portions of the base plate. Then the tabs of the annular support member are pressed by a correspondingly shaped tool in the direction of the base plate and the annular support member rotated by a small angle. As a result, the tabs engage in the recesses of the thickening (of the approach) of the base plate so that the annular retaining element can not turn back, but the tabs can spring back to their original shape without being under tension. An anti-rotation device for the burner seal itself is not necessary for general operating experience and is therefore not made possible by the here pitched assembly.

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 production of the combustion chamber and also later in the repair of damaged combustion chambers, the same reference points are available in the form of stubs for mechanical processing of the combustion chamber. Between production and overhaul of the combustion chamber, these approaches of thickening fulfill the function of a seal holder. During assembly, the burner seal is centered by a tool. The holder of the burner seal is also centered and moved by the tool. As a result, the installer 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 there are no joining processes necessary. This allows a precise, repeatable and easy and inexpensive installation. Due to the dead state of the holder in the locked state, it also comes in this no signs of fatigue in the operation of the engine. During the entire operating life of the burner seal this is kept close to the combustion chamber head. 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. The integrated feed hopper eliminates the need for an additional component for this function, which in turn would need to be reliably and operationally secured. The costs for the production and installation of an anti-rotation device are saved as 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.
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
1 is a schematic enlarged detail view of a combustion chamber according to the invention with associated components of the gas turbine,
Fig. 3
an enlarged detail sectional view in a schematic representation of an embodiment of the inventive solution,
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 FIGS. 5 and 6 , Another embodiment with mounted burner seal and holder, and
Fig. 8
simplified representations of 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 may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well. The engine 10 is conventionally formed and includes in the flow direction one after another an air inlet 11, a fan 12 circulating 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 nozzle 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 include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude. The compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of the high pressure turbine 16 and the intermediate pressure turbine 17, respectively.

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 array of fixed vanes 23 extending radially inward from the housing 21 into the housing annular flow channel through the turbines 16, 17, 18 protrude, and a subsequent arrangement of turbine blades 24 which project outwardly from a rotatable hub 27. The compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.

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 in a simplified schematic representation of the area of a combustion chamber 108 of a gas turbine. This comprises an inner combustion chamber housing 109 and an outer combustion chamber housing 110. Upstream of the combustion chamber 108, a combustion chamber head 107 is arranged, in which a burner 106 with arm and head is arranged. The air supply to the combustion chamber 8 via a front blower 101 (fan), which is driven by a drive shaft 102. To the drive shaft 102, a compressor 103 is also connected. The reference numeral 104 shows a side stream (bypass channel). The incoming air is passed through a compressor outlet guide 105 with diffuser. The flow exiting the combustion chamber 108 is performed by a turbine nozzle 111 and a turbine runner 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 detail view of an embodiment of the inventive solution. According to the invention, a base plate 113 is arranged at the upstream end region of the combustion chamber 108, which is provided with a recess which is delimited by a collar 118. Through the recess of the burner 106 is performed, as in the Fig. 1 and 2 is shown. The base plate 113 is provided with a projection 114 (thickening). The thickening 114 supports in a recess 115 a burner seal 116, which is annular, as known from the prior art. The burner seal 116 is held by a retaining element 117 (retaining ring), as 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 portion of the annular base plate 113, which is provided with the collar 118 which limits the recess 121 for the passage of the burner 106. Distributed around the circumference of the collar 118 are three lugs 114 (thickenings 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 a projection 114 with a recess 115. Die Fig. 6 shows the in Fig. 5 shown arrangement in the mounted state of the annular burner seal 116 and the retaining 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 at the radially outer region of the retaining ring 117, as in the right half of the Fig. 8 is shown. There are three circumferentially distributed locking tabs (tabs) 120 shown.

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 inserted into the recess 115 of the projection 114. It is thus shown the finished assembled state.

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 retaining ring 117, while the variant of the locking tab 120c is arranged on the inside of the retaining ring 117. The locking tabs 120b and 120c are each shown in the bent state.

Bezugszeichenliste:LIST OF REFERENCE NUMBERS

11
TriebwerksachseEngine axis
1010
GasturbinentriebwerkGas turbine engine
1111
Lufteinlassair intake
1212
im Gehäuse umlaufender Fanin the housing revolving fan
1313
ZwischendruckkompressorIntermediate pressure compressor
1414
HochdruckkompressorHigh pressure compressor
1515
Brennkammerncombustors
1616
HochdruckturbineHigh-pressure turbine
1717
ZwischendruckturbineIntermediate pressure turbine
1818
NiederdruckturbineLow-pressure turbine
1919
Abgasdüseexhaust nozzle
2020
Leitschaufelnvanes
2121
TriebwerksgehäuseEngine casing
2222
KompressorlaufschaufelnCompressor blades
2323
Leitschaufelnvanes
2424
Turbinenschaufelnturbine blades
2626
Kompressortrommel oder -scheibeCompressor drum or disc
2727
TurbinenrotornabeTurbinenrotornabe
2828
Abgaskonusexhaust cone
101101
Frontgebläse (Fan)Front fan (fan)
102102
Antriebswelledrive shaft
103103
Verdichtercompressor
104104
Nebenstromsidestream
105105
Verdichteraustrittsleitrad mit DiffuserCompressor outlet diffuser with diffuser
106106
Brenner mit Arm und KopfBurner with arm and head
107107
Brennkammerkopfbulkhead
108108
Brennkammercombustion chamber
109109
Inneres BrennkammergehäuseInner combustion chamber housing
110110
Äußeres BrennkammergehäuseOuter combustion chamber housing
111111
Turbinenleitradturbine nozzle
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
BrennerdichtungBrenner seal
117117
Halterung der Brennerdichtung / Halteelement / HalteringHolder of the burner seal / retaining element / retaining ring
118118
Kragen der Grundplatte 113 zur Auflage der Brennerdichtung 116Collar of the base plate 113 for supporting the burner seal 116th
119119
Abdeckung der Grundplatte 113Cover of the base plate 113
120a120a
Verriegelungslasche des Dichtungshalters 117Locking tab of the seal holder 117
120b120b
gebogene Variante der Verriegelungslasche, außen am Dichtungshalter 117curved variant of the locking tab, outside of the seal holder 117th
120c120c
gebogene Variante der Verriegelungslasche, innen am Dichtungshalter 117curved variant of the locking tab, inside the seal holder 117th
121121
Ausnehmungrecess

Claims (6)

Brennkammerkopf einer Gasturbine mit einer Grundplatte (113), welche mit einer zentrischen Ausnehmung (121) versehen ist, in welcher zumindest ein Brenner (106) angeordnet ist, wobei die Grundplatte (113) mit Wandungen der Brennkammer (108) verbunden ist, sowie mit einer den Brenner (106) zum Rand der Ausnehmung (121) abdichtenden Brennerdichtung (116), dadurch gekennzeichnet, dass die Brennerdichtung (116) stromauf der Grundplatte (113) angeordnet ist und gegen einen an der Grundplatte (113) ausgebildeten, den Rand der zentrischen Ausnehmung (121) bildenden Kragen (118) zur Anlage bringbar ist und dass ein Halteelement (117) der Brennerdichtung (116) in Form eines Blechrings ausgebildet ist und stromauf der Brennerdichtung (116) angeordnet ist und mit zumindest einem Ansatz (114) der Grundplatte (113) spannungsfrei in Eingriff ist.Combustion chamber head of a gas turbine with 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 with a burner seal (116) sealing the burner (106) to the edge of the recess (121), characterized in that the burner seal (116) is located upstream of the base plate (113) and against a rim formed on the base plate (113) a holding element (117) of the burner seal (116) is in the form of a sheet metal ring and upstream of the burner seal (116) is arranged and with at least one projection (114) of the Base plate (113) is tension-free engaged. Brennkammerkopf nach Anspruch 1, dadurch gekennzeichnet, dass das Halteelement (117) mit zumindest einer Verriegelungslasche (120a, 120b, 120c) versehen ist, welche mit dem Ansatz (114) spannungsfrei in Eingriff ist.Combustor head according to claim 1, characterized in that the retaining element (117) is provided with at least one locking tab (120a, 120b, 120c) which is in tension-free engagement with the boss (114). Brennkammerkopf nach Anspruch 2, dadurch gekennzeichnet, dass die Lasche (120a, 120b, 120c) am Innenrand des ringförmigen Halteelements (117) angeordnet ist.Combustor head according to claim 2, characterized in that the tab (120a, 120b, 120c) is arranged on the inner edge of the annular retaining element (117). Brennkammerkopf nach Anspruch 2, dadurch gekennzeichnet, dass die Lasche (120a, 120b, 120c) am Außenrand des ringförmigen Halteelements (117) angeordnet ist.Combustor head according to claim 2, characterized in that the tab (120a, 120b, 120c) is arranged on the outer edge of the annular retaining element (117). Brennkammerkopf nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass der Ansatz (114) mit zumindest einer Ausnehmung (115) zum Eingriff der Verriegelungslasche (120a, 120b, 120c) versehen ist.Combustor head according to one of claims 2 to 4, characterized in that the projection (114) is provided with at least one recess (115) for engagement of the locking tab (120a, 120b, 120c). Brennkammerkopf nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Brennerdichtung (113) an ihrer stromauf liegenden Seite zur Einführung des Brenners (106) trichterförmig ausgebildet ist.Combustor head according to one of claims 1 to 5, characterized in that the burner seal (113) is funnel-shaped on its upstream side for the introduction of the burner (106).
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US9222675B2 (en) 2015-12-29
US20120240595A1 (en) 2012-09-27

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