[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP2503246B1 - Segmented combustion chamber head - Google Patents

Segmented combustion chamber head Download PDF

Info

Publication number
EP2503246B1
EP2503246B1 EP12001992.2A EP12001992A EP2503246B1 EP 2503246 B1 EP2503246 B1 EP 2503246B1 EP 12001992 A EP12001992 A EP 12001992A EP 2503246 B1 EP2503246 B1 EP 2503246B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
head
accordance
segments
sealing element
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.)
Active
Application number
EP12001992.2A
Other languages
German (de)
French (fr)
Other versions
EP2503246A3 (en
EP2503246A2 (en
Inventor
Stefan Penz
Miklos Dr. Gerendas
Sermed Sadig
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2503246A2 publication Critical patent/EP2503246A2/en
Publication of EP2503246A3 publication Critical patent/EP2503246A3/en
Application granted granted Critical
Publication of EP2503246B1 publication Critical patent/EP2503246B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a combustion chamber head according to the features of the preamble of claim 1.
  • the invention relates to a combustor head of a gas turbine having a substantially annular outer combustion chamber wall and at least one substantially annular inner combustion chamber wall and a plurality of burners distributed around the circumference.
  • Prior art annular combustors include a combustor head which is radially bounded by the inner and outer combustor walls.
  • One known construction of the combustor head includes an end wall connected to the inner and outer combustor walls.
  • a heat shield is attached to the inside of the combustion chamber.
  • the heat shields are each positioned around the burner.
  • a sealing element is used for the movable recording of the injection nozzle. This is positioned by means of holders or between the heat shield and the combustion chamber wall. On the outside of the combustion chamber a dome-shaped end wall is attached.
  • the structure of a known from the prior art combustion chamber, in particular of the combustion chamber head, is in DE 44 27 222 A1 described ( Fig. 1 and 4 ).
  • the combustion chamber head consists of a dome-like end wall 101, a front plate 102 extending between the inner and outer combustion chamber walls 107 and 104, a plurality of heat shields 103, a plurality of burners 106 and a sealing element per burner 105. These components are known in the art interconnected, eg welding, screwing or jamming.
  • the heat shields 103 are typically made as segments around the burner positioned and connected to the front panel.
  • DE 100 48 864 A1 ( Fig. 2 and 3 ) also describes the structure of a combustion chamber head.
  • the dome-like end wall 101 is designed as a separate item and mechanically attached to the combustion chamber head.
  • the holding elements 108 act simultaneously as a holder for the dome-like end wall 101 and as a holder of the sealing elements 105th
  • the structural parts are designed as solid rings.
  • These known constructions consist of many individual components that must be mounted. In some cases, additional openings in the dome-shaped end wall are required for installation or this end wall is mounted in an additional operation. The known designs do not form a closed volume, which can be used to dampen acoustic vibrations.
  • the US 5,524,438 A shows a burner head of a gas turbine with a plurality of segmented, circumferentially arranged head segments.
  • the invention has for its object to provide a combustion chamber head of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and assembly. 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.
  • a plurality of segment-like, circumferentially arranged head segments are provided, whose number of the number of burners is equal and which in the radial direction between the inner combustion chamber wall and the extend outer combustion chamber wall.
  • the head segments extend in the circumferential direction between radial planes formed by burner center axes.
  • the invention thus describes a solution for constructing a segmented combustion chamber head, in particular for an annular combustion chamber of a gas turbine, in which an overall construction which is simple to produce and very easy to install is provided.
  • the mounted head segments according to the invention form a complete combustion chamber head, including the function of a front panel and the function of a heat shield.
  • the assembled form Head segments a damping volume, which is particularly suitable for soundproofing.
  • the low number of individual components simplifies assembly. Likewise, maintenance and inspection work is easier and less expensive to carry out.
  • the intermediate regions between adjacent head segments are preferably each sealed by at least one sealing element.
  • This may preferably be annular and enclose the burner. It is particularly advantageous if the sealing element is guided in grooves of the burner and / or the head element and thus held and positioned. Remaining radially outer or radially inner intermediate areas can be sealed by additional sealing elements in a simple manner. It is also possible, for example, to provide a fin and a deformable element. Furthermore, it is possible to provide for sealing labyrinth seal-like elements.
  • the solution according to the invention reduces the complexity of the combustion chamber head by combining the combustion chamber head segments with different functions of the individual parts of the conventional combustion chamber head. Furthermore, this construction offers the possibility of providing the volume necessary for damping acoustic vibrations. The operation of such damper is in the DE 10 2009 032 277 A1 described. The required closed volume is provided within a header segment.
  • the Fig. 5 . 6 and 7 show a combustion chamber head, which is not from an annular head element but according to the invention of a plurality of head segments, 201 corresponding to the number of burners 106, constructed. These head segments 201 extend in the radial direction between the inner and outer combustion chamber wall 107 and 104 and are mechanically connected there in a known manner, eg with screws. In the circumferential direction, the head segments 201 each extend in an area between two burners 106. The circumferential division thus always takes place in the burner center axis 208.
  • the movable sealing elements 105 which seal the area around the burner 106 against uncontrolled entry of the compressor air into the combustion chamber 15 and at the same time allow relative movement between burner 106 and combustion head 35 are stored in slots which are integrated in the head segments 201. This reduces the assembly effort and the number of small parts. At the same time, a large area of the gap between two segments is sealed. In the area between the sealing element 105 and the inner or outer combustion chamber wall 107 and 104, the remaining gap is sealed with a sealing strip 202 against uncontrolled air inlet.
  • the gap can also be sealed with a specially shaped sealing element with extensions 203. ( Fig. 8 ).
  • the leakage air flow may also be controlled with a labyrinth 204 formed on the side surfaces of the head segments 201. ( Fig. 9 ).
  • Another possibility of sealing is the formation of mating surfaces on the side walls of the head segments 201.
  • Another possibility of sealing is the formation of one or more fins 206 on one side of the head segment and the application of a readily deformable material 205 on the opposite side of the head segment.
  • This material may be, for example, a metal foam, as in DE 10 360 164 A1 described. ( Fig. 10 ).
  • the assembly of the combustion chamber head is carried out by mating the sealing elements 105, the sealing strip 202 and the head segments 201 to a full ring. Then, the inner and outer combustion chamber walls 107 and 104 are connected to the head segments 201, whereby the sealing members 105 and sealing strips 202 are movably held in position.
  • the socket 207 for receiving the pin can be integrated into individual or all head segments 201 ( Figure 11 ).
  • Fig. 12 shows a schematic representation of a gas turbine engine according to the present invention.
  • 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 outward from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and intermediate pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting 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. 13 schematically shows compressor outlet blades 31 through which compressor air is introduced into a combustion chamber housing.
  • This comprises a combustion chamber outer housing 32 and a combustion chamber inner housing 33.
  • a burner with arm and head (reference numeral 34) is provided.
  • the reference numeral 35 schematically shows a combustion chamber head, to which a combustion chamber wall 36 connects.
  • the reference numeral 37 schematically turbine inlet blades are shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung bezieht sich auf einen Brennkammerkopf gemäß den Merkmalen des Oberbegriffs des Anspruches 1.The invention relates to a combustion chamber head according to the features of the preamble of claim 1.

Im Einzelnen bezieht sich die Erfindung auf einen Brennkammerkopf einer Gasturbine mit einer im Wesentlichen ringförmigen äußeren Brennkammerwand und mit zumindest einer im Wesentlichen ringförmigen inneren Brennkammerwand sowie mit mehreren um den Umfang verteilt angeordneten Brennern.In particular, the invention relates to a combustor head of a gas turbine having a substantially annular outer combustion chamber wall and at least one substantially annular inner combustion chamber wall and a plurality of burners distributed around the circumference.

Ringbrennkammern nach dem Stand der Technik umfassen einen Brennkammerkopf, welcher radial von der inneren und äußeren Brennkammerwand begrenzt wird.Prior art annular combustors include a combustor head which is radially bounded by the inner and outer combustor walls.

Ein bekannter Aufbau des Brennkammerkopfes umfasst eine Abschlusswand, welche mit der inneren und äußeren Brennkammerwand verbunden ist.One known construction of the combustor head includes an end wall connected to the inner and outer combustor walls.

An dieser Abschlusswand wird auf der Brennkammerinnenseite ein Hitzeschild angebracht. Die Hitzeschilde sind jeweils um den Brenner herum positioniert.At this end wall, a heat shield is attached to the inside of the combustion chamber. The heat shields are each positioned around the burner.

Zur beweglichen Aufnahme der Einspritzdüse wird ein Dichtelement verwendet. Dieses wird mittels Haltern oder zwischen Hitzeschild und Brennkammerwand positioniert. Auf der Brennkammeraußenseite ist eine domartige Abschlusswand angebracht.For the movable recording of the injection nozzle, a sealing element is used. This is positioned by means of holders or between the heat shield and the combustion chamber wall. On the outside of the combustion chamber a dome-shaped end wall is attached.

Im Folgenden werden aus dem Stand der Technik bekannte Konstruktionen im Zusammenhang mit den Fig. 1 bis 4 beschrieben.In the following, known from the prior art constructions in connection with the Fig. 1 to 4 described.

Der Aufbau einer aus dem Stand der Technik bekannten Brennkammer, insbesondere des Brennkammerkopfes, ist in DE 44 27 222 A1 beschrieben (Fig. 1 und 4). Der Brennkammerkopf besteht aus einer domartigen Abschlusswand 101, einer Frontplatte 102, die sich zwischen der inneren und äußeren Brennkammerwand 107 und 104 erstreckt, einer Mehrzahl von Hitzeschilden 103, einer Mehrzahl von Brennern 106 sowie einem Dichtelement pro Brenner 105. Diese Bauteile werden auf bekannte Art miteinander verbunden, z.B. Verschweißen, Verschrauben oder Verklemmen. Die Hitzeschilde 103 werden in der Regel als Segmente ausgeführt, um den Brenner herum positioniert und mit der Frontplatte verbunden. DE 100 48 864 A1 (Fig. 2 und 3) beschreibt ebenfalls den Aufbau eines Brennkammerkopfes. Hier wird die domartige Abschlusswand 101 als separates Einzelteil ausgeführt und mechanisch am Brennkammerkopf befestigt. Hier fungieren die Halteelemente 108 gleichzeitig als Halter für die domartige Abschlusswand 101 und als Halter der Dichtelemente 105.
Bei allen Konstruktionen sind die Strukturteile als Vollringe ausgeführt.
Diese bekannten Konstruktionen bestehen aus vielen Einzelkomponenten, die montiert werden müssen. Teilweise sind zur Montage zusätzlich Öffnungen in der domartigen Abschlusswand notwendig oder diese Abschlusswand wird in einem zusätzlichen Arbeitsgang montiert. Die bekannten Ausführungen bilden kein abgeschlossenes Volumen, welches zur Dämpfung von akustischen Schwingungen genutzt werden kann.
Die US 5,524,438 A zeigt einen Brennerkopf einer Gasturbine mit mehreren segmentartigen, um den Umfang angeordneten Kopfsegmenten. Diese sind, in Umfangsrichtung gesehen, jeweils in einer Mittelebene zwischen den Brennerachsen geteilt. Weiterhin sind die Kopfsegmente nochmals in radialer Richtung auf einer die Brennerachsen umfassenden Kreislinie unterteilt.
Die EP 1 818 615 A1 beschreibt einen Aufbau, bei welchem die einzelnen Kopfsegmente ebenfalls in Umfangsrichtung in einer Mittelebene zwischen den Brennerachsen geteilt sind.
Der Erfindung liegt die Aufgabe zugrunde, einen Brennkammerkopf der eingangs genannten Art zu schaffen, welcher bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit und Montierbarkeit die Nachteile des Standes der Technik vermeidet.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.The structure of a known from the prior art combustion chamber, in particular of the combustion chamber head, is in DE 44 27 222 A1 described ( Fig. 1 and 4 ). The combustion chamber head consists of a dome-like end wall 101, a front plate 102 extending between the inner and outer combustion chamber walls 107 and 104, a plurality of heat shields 103, a plurality of burners 106 and a sealing element per burner 105. These components are known in the art interconnected, eg welding, screwing or jamming. The heat shields 103 are typically made as segments around the burner positioned and connected to the front panel. DE 100 48 864 A1 ( Fig. 2 and 3 ) also describes the structure of a combustion chamber head. Here, the dome-like end wall 101 is designed as a separate item and mechanically attached to the combustion chamber head. Here, the holding elements 108 act simultaneously as a holder for the dome-like end wall 101 and as a holder of the sealing elements 105th
In all constructions, the structural parts are designed as solid rings.
These known constructions consist of many individual components that must be mounted. In some cases, additional openings in the dome-shaped end wall are required for installation or this end wall is mounted in an additional operation. The known designs do not form a closed volume, which can be used to dampen acoustic vibrations.
The US 5,524,438 A shows a burner head of a gas turbine with a plurality of segmented, circumferentially arranged head segments. These are, as seen in the circumferential direction, each divided in a central plane between the burner axes. Furthermore, the head segments are again divided in the radial direction on a circular axis surrounding the burner axes.
The EP 1 818 615 A1 describes a structure in which the individual head segments are also divided in the circumferential direction in a median plane between the burner axes.
The invention has for its object to provide a combustion chamber head of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and assembly.
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.

Es ist vorgesehen, dass mehrere segmentartige, um den Umfang angeordnete Kopfsegmente vorgesehen sind, deren Anzahl der Zahl der Brenner gleich ist und welche sich in radialer Richtung zwischen der inneren Brennkammerwand und der äußeren Brennkammerwand erstrecken. Erfindungsgemäß, erstrecken sich die Kopfsegmente in Umfangsrichtung zwischen durch Brennermittelachsen gebildete Radialebenen.It is envisaged that a plurality of segment-like, circumferentially arranged head segments are provided, whose number of the number of burners is equal and which in the radial direction between the inner combustion chamber wall and the extend outer combustion chamber wall. According to the invention, the head segments extend in the circumferential direction between radial planes formed by burner center axes.

Die Erfindung beschreibt somit eine Lösung zum Aufbau eines segmentierten Brennkammerkopfes, insbesondere für eine Ringbrennkammer einer Gasturbine, bei welchem eine einfach herzustellende und sehr einfach zu montierende Gesamtkonstruktion vorgesehen ist. Die montierten Kopfsegmente bilden erfindungsgemäß einen vollständigen Brennkammerkopf, inkl. der Funktion einer Frontplatte und der Funktion eines Hitzeschildes. Weiterhin bilden die montierten Kopfsegmente ein Dämpfungsvolumen, welches zur Schalldämpfung besonders geeignet ist. Durch die geringe Zahl an Einzelkomponenten vereinfacht sich die Montage. Ebenso sind Wartungs- und Kontrollarbeiten einfacher und mit geringerem Aufwand durchführbar.The invention thus describes a solution for constructing a segmented combustion chamber head, in particular for an annular combustion chamber of a gas turbine, in which an overall construction which is simple to produce and very easy to install is provided. The mounted head segments according to the invention form a complete combustion chamber head, including the function of a front panel and the function of a heat shield. Furthermore, the assembled form Head segments a damping volume, which is particularly suitable for soundproofing. The low number of individual components simplifies assembly. Likewise, maintenance and inspection work is easier and less expensive to carry out.

Da die einzelnen Kopfsegmente sich mit ihren Trennebenen (Umfangs-Begrenzungskanten) in der Brennermittelachse bzw. in einer durch die Brennermittelachse und die Triebwerksachse definierten Radialebene fügen, ergibt sich auch hinsichtlich der thermischen Ausdehnungen und der dadurch hervorgerufenen mechanischen Belastungen eine vorteilhafte Konstruktion. Die Zwischenbereiche zwischen benachbarten Kopfsegmenten sind bevorzugterweise jeweils durch zumindest ein Dichtungselement abgedichtet. Dieses kann bevorzugterweise ringförmig ausgebildet sein und den Brenner umschließen. Dabei ist es besonders vorteilhaft, wenn das Dichtungselement in Nuten des Brenners und/oder des Kopfelements geführt ist und somit gehalten und positioniert wird. Verbleibende radial außenliegende oder radial innenliegende Zwischenbereiche können durch zusätzliche Dichtungselemente in einfacher Weise abgedichtet werden. Hierbei ist es beispielsweise auch möglich, eine Finne sowie ein deformierbares Element vorzusehen. Weiterhin ist es möglich, zur Abdichtung labyrinthdichtungsartige Elemente vorzusehen.Since the individual head segments fit with their parting planes (peripheral boundary edges) in the burner center axis or in a radial plane defined by the burner center axis and the engine axis, an advantageous construction also results with regard to the thermal expansions and the mechanical loads caused thereby. The intermediate regions between adjacent head segments are preferably each sealed by at least one sealing element. This may preferably be annular and enclose the burner. It is particularly advantageous if the sealing element is guided in grooves of the burner and / or the head element and thus held and positioned. Remaining radially outer or radially inner intermediate areas can be sealed by additional sealing elements in a simple manner. It is also possible, for example, to provide a fin and a deformable element. Furthermore, it is possible to provide for sealing labyrinth seal-like elements.

Die erfindungsgemäße Lösung verringert die Komplexität des Brennkammerkopfes, indem die Brennkammer-Kopfsegmente verschiedene Funktionen der Einzelteile des herkömmlichen Brennkammerkopfes vereinen. Des Weiteren bietet diese Konstruktion die Möglichkeit, das zur Dämpfung akustischer Schwingungen notwendige Volumen bereitzustellen. Die Funktionsweise solcher Dämpfer ist in der DE 10 2009 032 277 A1 beschrieben. Das dafür notwendige abgeschlossene Volumen wird innerhalb eines Kopfsegmentes bereitgestellt.The solution according to the invention reduces the complexity of the combustion chamber head by combining the combustion chamber head segments with different functions of the individual parts of the conventional combustion chamber head. Furthermore, this construction offers the possibility of providing the volume necessary for damping acoustic vibrations. The operation of such damper is in the DE 10 2009 032 277 A1 described. The required closed volume is provided within a header segment.

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

Fig. 1
eine vereinfachte Axial-Teilschnittansicht eines aus dem Stand der Technik bekannten Brennkammerkopfes,
Fig. 2
eine Ansicht, analog Fig. 1, eines weiteren aus dem Stand der Technik bekannten Brennkammerkopfes,
Fig. 3
eine perspektivische Teilansicht der in Fig. 2 gezeigten Konstruktion gemäß dem Stand der Technik,
Fig. 4
eine Detaildarstellung der Hitzeschilder gemäß dem Stand der Technik analog der in Fig. 1 gezeigten Konstruktion,
Fig. 5
eine Teilansicht eines ersten Ausführungsbeispiels der erfindungsgemäßen Ausgestaltung eines Kopfelements mit Dichtungselementen,
Fig. 6
Ansichten der in Fig. 5 gezeigten erfindungsgemäßen Lösung im montierten Zustand in Strömungsrichtung (obere Bildhälfte der Fig. 6) und entgegen der Strömungsrichtung (untere Bildhälfte der Fig. 6),
Fig. 7
eine Axial-Teilschnittansicht, analog der Darstellungen der Fig. 1 und 2 des in den Fig. 5 und 6 gezeigten Ausführungsbeispiels,
Fig. 8
vereinfachte Darstellungen eines weiteren Ausführungsbeispiels eines Dichtungselements mit Verlängerungen sowie Montagemöglichkeiten,
Fig. 9
eine vereinfachte Darstellung eines weiteren Ausführungsbeispiels einer erfindungsgemäß einsetzbaren Dichtung,
Fig. 10
eine vereinfachte Darstellung eines weiteren Ausführungsbeispiels einer erfindungsgemäß einsetzbaren Dichtung,
Fig. 11
vereinfachte Darstellungen in Teil-Ansichten eines weiteren Ausführungsbeispiels der Erfindung mit Buchse und Führungsstift,
Fig. 12
eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung, und
Fig. 13
eine schematische Axial-Teilschnittansicht einer erfindungsgemäßen Gasturbinenbrennkammer.
In the following the invention will be described by means of embodiments in conjunction with the drawing. Showing:
Fig. 1
2 is a simplified partial axial sectional view of a known from the prior art combustion chamber head,
Fig. 2
a view, analog Fig. 1 another known from the prior art combustion chamber head,
Fig. 3
a partial perspective view of in Fig. 2 shown construction according to the prior art,
Fig. 4
a detailed representation of the heat shields according to the prior art analogous to in Fig. 1 shown construction,
Fig. 5
a partial view of a first embodiment of the inventive design of a header with sealing elements,
Fig. 6
Views of in Fig. 5 shown solution according to the invention in the assembled state in the flow direction (upper half of the Fig. 6 ) and against the flow direction (lower half of the Fig. 6 )
Fig. 7
an axial partial sectional view, analogous to the representations of Fig. 1 and 2 in the Fig. 5 and 6 shown embodiment,
Fig. 8
simplified representations of a further embodiment of a sealing element with extensions and mounting options,
Fig. 9
a simplified representation of another embodiment of an inventively usable seal,
Fig. 10
a simplified representation of another embodiment of an inventively usable seal,
Fig. 11
simplified representations in partial views of a further embodiment of the invention with socket and guide pin,
Fig. 12
a schematic representation of a gas turbine engine according to the present invention, and
Fig. 13
a schematic axial partial sectional view of a gas turbine combustor according to the invention.

Die Fig. 5, 6 und 7 zeigen einen Brennkammerkopf, der nicht aus einem ringförmigen Kopfelement sondern erfindungsgemäß aus einer Vielzahl von Kopfsegmenten, 201 entsprechend der Anzahl der Brenner 106, aufgebaut ist. Diese Kopfsegmente 201 erstrecken sich in radialer Richtung zwischen der inneren und äußeren Brennkammerwand 107 und 104 und werden dort auf bekannte Art, z.B. mit Schrauben, mechanisch verbunden. In Umfangsrichtung erstrecken sich die Kopfsegmente 201 jeweils in einem Bereich zwischen zwei Brennern 106. Die Umfangsteilung erfolgt also immer in der Brennermittelachse 208. Die beweglichen Dichtelemente 105, die den Bereich um den Brenner 106 gegen unkontrolliertes Eintreten der Kompressorluft in die Brennkammer 15 abdichten und gleichzeitig eine relative Bewegung zwischen Brenner 106 und Brennkammerkopf 35 erlauben, werden in Schlitzen gelagert, die in den Kopfsegmenten 201 integriert sind. Das verringert den Montageaufwand und die Anzahl der Kleinteile. Gleichzeitig wird ein großer Bereich des Spaltes zwischen zwei Segmenten abgedichtet. In dem Bereich zwischen dem Dichtelement 105 und der inneren bzw. äußeren Brennkammerwand 107 bzw. 104 wird der verbleibende Spalt mit einem Dichtstreifen 202 gegen unkontrollierten Lufteintritt abgedichtet.The Fig. 5 . 6 and 7 show a combustion chamber head, which is not from an annular head element but according to the invention of a plurality of head segments, 201 corresponding to the number of burners 106, constructed. These head segments 201 extend in the radial direction between the inner and outer combustion chamber wall 107 and 104 and are mechanically connected there in a known manner, eg with screws. In the circumferential direction, the head segments 201 each extend in an area between two burners 106. The circumferential division thus always takes place in the burner center axis 208. The movable sealing elements 105, which seal the area around the burner 106 against uncontrolled entry of the compressor air into the combustion chamber 15 and at the same time allow relative movement between burner 106 and combustion head 35 are stored in slots which are integrated in the head segments 201. This reduces the assembly effort and the number of small parts. At the same time, a large area of the gap between two segments is sealed. In the area between the sealing element 105 and the inner or outer combustion chamber wall 107 and 104, the remaining gap is sealed with a sealing strip 202 against uncontrolled air inlet.

Alternativ kann der Spalt auch mit einem speziell geformten Dichtelement mit Verlängerungen 203 abgedichtet werden. (Fig. 8).Alternatively, the gap can also be sealed with a specially shaped sealing element with extensions 203. ( Fig. 8 ).

Alternativ kann der Leckageluftstrom auch mit einem Labyrinth 204, welches an den Seitenflächen der Kopfsegmente 201 ausgebildet ist, kontrolliert werden. (Fig. 9).Alternatively, the leakage air flow may also be controlled with a labyrinth 204 formed on the side surfaces of the head segments 201. ( Fig. 9 ).

Eine weitere Möglichkeit der Abdichtung ist die Ausbildung von Passflächen an den Seitenwänden der Kopfsegmente 201.Another possibility of sealing is the formation of mating surfaces on the side walls of the head segments 201.

Eine weitere Möglichkeit der Abdichtung ist die Ausbildung einer oder mehrerer Finnen 206 auf einer Seite des Kopfsegmentes und das Aufbringen eines leicht deformierbaren Materials 205 auf der gegenüberliegenden Seite des Kopfsegmentes. Dieses Material kann z.B. ein Metallschaum sein, wie in DE 10 360 164 A1 beschrieben. (Fig. 10).Another possibility of sealing is the formation of one or more fins 206 on one side of the head segment and the application of a readily deformable material 205 on the opposite side of the head segment. This material may be, for example, a metal foam, as in DE 10 360 164 A1 described. ( Fig. 10 ).

Die Montage des Brennkammerkopfes erfolgt durch Zusammenstecken der Dichtelemente 105, der Dichtstreifen 202 und der Kopfsegmente 201 zu einem vollen Ring. Dann werden die innere und äußere Brennkammerwand 107 und 104 mit den Kopfsegmenten 201 verbunden, wodurch die Dichtelemente 105 und Dichtstreifen 202 beweglich in der Position gehalten werden.The assembly of the combustion chamber head is carried out by mating the sealing elements 105, the sealing strip 202 and the head segments 201 to a full ring. Then, the inner and outer combustion chamber walls 107 and 104 are connected to the head segments 201, whereby the sealing members 105 and sealing strips 202 are movably held in position.

Im Falle einer vorderen Brennkammeraufhängung mit einem Führungsstift 108, wie in GB 2 147 405 A beschrieben, kann die Buchse 207 zur Aufnahme des Stiftes in einzelne oder alle Kopfsegmente 201 integriert werden (Fig.11).In the case of a front combustion chamber suspension with a guide pin 108, as in GB 2 147 405 A described, the socket 207 for receiving the pin can be integrated into individual or all head segments 201 ( Figure 11 ).

Fig. 12 zeigt eine schematische Darstellung eines Gasturbinentriebwerks gemäß der vorliegenden Erfindung. Fig. 12 shows a schematic representation of a gas turbine engine according to the present invention.

Das Gasturbinentriebwerk 10 gemäß Fig. 12 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. 12 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 outward from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and 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 stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting 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. 13 zeigt in schematischer Weise Kompressorauslassschaufeln 31, durch welche Verdichterluft in ein Brennkammergehäuse eingeleitet wird. Dieses umfasst ein Brennkammeraußengehäuse 32 sowie ein Brennkammerinnengehäuse 33. Weiterhin ist ein Brenner mit Arm und Kopf (Bezugszeichen 34) vorgesehen. Das Bezugszeichen 35 zeigt in schematischer Weise einen Brennkammerkopf, an welchen sich eine Brennkammerwand 36 anschließt. Mit dem Bezugszeichen 37 sind schematisch Turbineneinlassschaufeln dargestellt.The Fig. 13 schematically shows compressor outlet blades 31 through which compressor air is introduced into a combustion chamber housing. This comprises a combustion chamber outer housing 32 and a combustion chamber inner housing 33. Furthermore, a burner with arm and head (reference numeral 34) is provided. The reference numeral 35 schematically shows a combustion chamber head, to which a combustion chamber wall 36 connects. The reference numeral 37 schematically turbine inlet blades are shown.

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
3131
KompressorauslassschaufelnKompressorauslassschaufeln
3232
BrennkammeraußengehäuseCombustion chamber outer housing
3333
BrennkammerinnengehäuseCombustion chamber inner housing
3434
Brenner mit Arm und KopfBurner with arm and head
3535
Brennkammerkopfbulkhead
3636
Brennkammerwandcombustion chamber wall
3737
TurbineneinlassschaufelnTurbine inlet vanes
101101
domartige Abschlusswanddome-shaped end wall
102102
Frontplattefront panel
103103
Hitzeschildheat shield
104104
äußere Brennkammerwandouter combustion chamber wall
105105
Dichtelementsealing element
106106
Brennerburner
107107
innere Brennkammerwandinner combustion chamber wall
108108
Halteelement/FührungsstiftRetaining member / guide pin
201201
Kopfsegmenthead segment
202202
Dichtstreifensealing strips
203203
Dichtelement mit VerlängerungSealing element with extension
204204
Labyrinthlabyrinth
205205
deformierbares Material/Elementdeformable material / element
206206
Finnefin
207207
integrierte Buchseintegrated socket
208208
BrennermittelachseBurner central axis
209209
Radialebeneradial plane

Claims (10)

  1. Combustion chamber head of a gas turbine with a substantially annular outer combustion chamber wall (104) and with at least one substantially annular inner combustion chamber wall (107), and with several burners (106) distributed over the circumference, wherein several segment-like head segments (201) are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall (107) and the outer combustion chamber wall (108), characterized in that the head segments (201) extend in the circumferential direction between radial planes (209) formed by central burner axes (208).
  2. Combustion chamber head in accordance with Claim 1, characterized in that between the burner (106) and the head element (201) at least one sealing element (105, 202, 203) is arranged.
  3. Combustion chamber head in accordance with Claim 2, characterized in that the sealing element (105, 203) is substantially annularly designed.
  4. Combustion chamber head in accordance with Claim 2 or 3, characterized in that the sealing element (105, 202, 203) is at least partly arranged in grooves of the burner (106) and/ or of the head element (201).
  5. Combustion chamber head in accordance with one of the Claims 2 to 4, characterized in that the sealing element includes at least one fin (206) and a deformable element (205) that can be brought in interaction with the latter.
  6. Combustion chamber head in accordance with one of the Claims 2 to 5, characterized in that the sealing element includes at least one labyrinth seal (204).
  7. Combustion chamber head in accordance with one of the Claims 1 to 6, characterized in that the head segment (201) includes at least one bushing (207) for interaction with at least one holding element (108).
  8. Combustion chamber head in accordance with one of the Claims 1 to 7, characterized in that the head segments (201) in the assembled state form at least one dampening volume.
  9. Combustion chamber head in accordance with one of the Claims 1 to 8, characterized in that the head segments (201) in the assembled state form a combustion chamber head in particular with a front plate (102) and a thermal shield (103).
  10. Combustion chamber head in accordance with one of the Claims 1 to 9, characterized in that the head segments (201) in the assembled state are tightly - or with defined openings - connected to the outer combustion chamber wall (104) and to the inner combustion chamber wall (107).
EP12001992.2A 2011-03-22 2012-03-21 Segmented combustion chamber head Active EP2503246B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011014670A DE102011014670A1 (en) 2011-03-22 2011-03-22 Segmented combustion chamber head

Publications (3)

Publication Number Publication Date
EP2503246A2 EP2503246A2 (en) 2012-09-26
EP2503246A3 EP2503246A3 (en) 2014-11-26
EP2503246B1 true EP2503246B1 (en) 2018-12-05

Family

ID=45932099

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12001992.2A Active EP2503246B1 (en) 2011-03-22 2012-03-21 Segmented combustion chamber head

Country Status (3)

Country Link
US (1) US9328926B2 (en)
EP (1) EP2503246B1 (en)
DE (1) DE102011014670A1 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10378775B2 (en) * 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
US9498850B2 (en) * 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
DE102013222863A1 (en) 2013-11-11 2015-05-13 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor and method for its production
US9677767B2 (en) * 2014-05-29 2017-06-13 Siemens Energy, Inc. Combustion turbine with Siamesed wall paired combustor housings
US9625152B2 (en) 2014-06-03 2017-04-18 Pratt & Whitney Canada Corp. Combustor heat shield for a gas turbine engine
US9534785B2 (en) * 2014-08-26 2017-01-03 Pratt & Whitney Canada Corp. Heat shield labyrinth seal
CN109563994B (en) * 2016-07-25 2020-12-01 西门子股份公司 Gas turbine engine with resonator ring
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
US10724739B2 (en) 2017-03-24 2020-07-28 General Electric Company Combustor acoustic damping structure
US10415480B2 (en) 2017-04-13 2019-09-17 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US11242804B2 (en) * 2017-06-14 2022-02-08 General Electric Company Inleakage management apparatus
US11149948B2 (en) 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports
US10774685B2 (en) * 2018-04-30 2020-09-15 Ratheon Technologies Corporation Gas turbine engine exhaust component
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
US11156162B2 (en) 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
US10823415B2 (en) * 2018-06-01 2020-11-03 Raytheon Technologies Corporation Deflector for combustor of gas turbine engine
US11506125B2 (en) 2018-08-01 2022-11-22 General Electric Company Fluid manifold assembly for gas turbine engine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2107448B (en) 1980-10-21 1984-06-06 Rolls Royce Gas turbine engine combustion chambers
GB2147405A (en) 1983-09-28 1985-05-09 Rolls Royce Gas turbine engine combustion chamber mounting
DE4427222A1 (en) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US5524438A (en) 1994-12-15 1996-06-11 United Technologies Corporation Segmented bulkhead liner for a gas turbine combustor
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
DE10048864A1 (en) 2000-10-02 2002-04-11 Rolls Royce Deutschland Combustion chamber head for a gas turbine
DE10360164A1 (en) 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gas turbine component
FR2897417A1 (en) * 2006-02-10 2007-08-17 Snecma Sa ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE
FR2903171B1 (en) * 2006-06-29 2008-10-17 Snecma Sa CRABOT LINK ARRANGEMENT FOR TURBOMACHINE COMBUSTION CHAMBER
FR2914399B1 (en) 2007-03-27 2009-10-02 Snecma Sa FURNITURE FOR BOTTOM OF COMBUSTION CHAMBER.
US8015815B2 (en) * 2007-04-18 2011-09-13 Parker-Hannifin Corporation Fuel injector nozzles, with labyrinth grooves, for gas turbine engines
FR2918443B1 (en) 2007-07-04 2009-10-30 Snecma Sa COMBUSTION CHAMBER COMPRISING THERMAL PROTECTION DEFLECTORS OF BOTTOM BOTTOM AND GAS TURBINE ENGINE BEING EQUIPPED
FR2935465B1 (en) * 2008-08-29 2013-09-20 Snecma FIXING A CMC DEFLECTOR ON A BOTTOM BOTTOM BY PINCING USING A METAL SUPPORT.
US8104290B2 (en) * 2008-10-15 2012-01-31 Alstom Technology Ltd. Combustion liner damper
JP4815513B2 (en) * 2009-07-06 2011-11-16 川崎重工業株式会社 Gas turbine combustor
DE102009032277A1 (en) 2009-07-08 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head of a gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2503246A3 (en) 2014-11-26
EP2503246A2 (en) 2012-09-26
DE102011014670A1 (en) 2012-09-27
US20120240583A1 (en) 2012-09-27
US9328926B2 (en) 2016-05-03

Similar Documents

Publication Publication Date Title
EP2503246B1 (en) Segmented combustion chamber head
EP2960438B1 (en) Variable guide vane device for a gas turbine and gas turbine equipped with such a device
EP2522831B1 (en) Turbojet engine with oil cooler in the engine nacelle
EP3056813B1 (en) Seal of an edge gap between effusion shingle of a gas turbine combustor
EP2845999B1 (en) Method for balancing and for mounting a turbine rotor
EP2881552B1 (en) Aircraft gas turbine having a core engine housing with cooling air tubes
EP2918913B1 (en) Combustion chamber of a gas turbine
DE102012007129A1 (en) Guide vane adjusting a gas turbine
EP2824282A1 (en) Gas turbine with high pressure turbine cooling system
EP2543865A2 (en) Turbofan engine with heat exchanger on the core engine housing
EP2799776A1 (en) Burner seal for gas turbine combustion chamber head and heat shield
DE102014220317A1 (en) Aircraft gas turbine engine with shock absorbing element for fan blade loss
DE102014204466A1 (en) Combustion chamber of a gas turbine
DE102014213302A1 (en) Combustion chamber of a gas turbine with screwed combustion chamber head
DE102014204476A1 (en) Combustion chamber of a gas turbine
EP2503242A2 (en) Combustion chamber head with holder for burner seals in gas turbines
DE102011016917A1 (en) Gas turbine combustor with a holder of a seal for an attachment
EP3321589B1 (en) Fuel nozzle of a gas turbine with swirl creator
EP2831379B1 (en) Holder ring
DE102013226490A1 (en) Chilled flange connection of a gas turbine engine
DE102014214775A1 (en) Aircraft gas turbine with a seal for sealing a spark plug on the combustion chamber wall of a gas turbine
DE102016212649A1 (en) Burner seal of a gas turbine and method for its production
DE102012014109A1 (en) Washer seal for use in gas turbine engine, has sealing ring, which is arranged between radially outer sections of rotor disks and is clamped between rotor disks in axial direction, where sealing elements are arranged on sealing ring
DE102013220455A1 (en) Gas turbine engine with cooling air ring chamber
DE102011008919A1 (en) Aircraft gas turbine thrust reverser

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

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

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/00 20060101AFI20141023BHEP

Ipc: F23R 3/60 20060101ALI20141023BHEP

Ipc: F23R 3/28 20060101ALI20141023BHEP

17P Request for examination filed

Effective date: 20150325

RBV Designated contracting states (corrected)

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180621

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PENZ, STEFAN

Inventor name: GERENDAS, MIKLOS, DR.

Inventor name: SADIG, SERMED

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1073533

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181215

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502012013926

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20181205

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: FI

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

Effective date: 20181205

Ref country code: BG

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

Effective date: 20190305

Ref country code: HR

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

Effective date: 20181205

Ref country code: LV

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

Effective date: 20181205

Ref country code: ES

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

Effective date: 20181205

Ref country code: LT

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

Effective date: 20181205

Ref country code: NO

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

Effective date: 20190305

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

Ref country code: AL

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

Effective date: 20181205

Ref country code: RS

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

Effective date: 20181205

Ref country code: GR

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

Effective date: 20190306

Ref country code: SE

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

Effective date: 20181205

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

Ref country code: NL

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

Effective date: 20181205

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

Ref country code: PT

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

Effective date: 20190405

Ref country code: CZ

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

Effective date: 20181205

Ref country code: IT

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

Effective date: 20181205

Ref country code: PL

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

Effective date: 20181205

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

Ref country code: SK

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

Effective date: 20181205

Ref country code: RO

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

Effective date: 20181205

Ref country code: IS

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

Effective date: 20190405

Ref country code: SM

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

Effective date: 20181205

Ref country code: EE

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

Effective date: 20181205

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502012013926

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

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

Ref country code: SI

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

Effective date: 20181205

Ref country code: DK

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

Effective date: 20181205

Ref country code: MC

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

Effective date: 20181205

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20190906

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

Ref country code: LU

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

Effective date: 20190321

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190331

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

Ref country code: LI

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

Effective date: 20190331

Ref country code: CH

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

Effective date: 20190331

Ref country code: IE

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

Effective date: 20190321

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

Ref country code: BE

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

Effective date: 20190331

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

Ref country code: TR

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

Effective date: 20181205

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

Ref country code: GB

Payment date: 20200327

Year of fee payment: 9

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

Ref country code: MT

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

Effective date: 20181205

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1073533

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190321

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

Ref country code: AT

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

Effective date: 20190321

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

Ref country code: CY

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

Effective date: 20181205

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

Ref country code: HU

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

Effective date: 20120321

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

Effective date: 20210321

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

Ref country code: GB

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

Effective date: 20210321

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

Ref country code: MK

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

Effective date: 20181205

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

Ref country code: FR

Payment date: 20230323

Year of fee payment: 12

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

Ref country code: DE

Payment date: 20230328

Year of fee payment: 12

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230528