EP2846002A1 - Gas turbine - Google Patents

Gas turbine Download PDF

Info

Publication number
EP2846002A1
EP2846002A1 EP14150517.2A EP14150517A EP2846002A1 EP 2846002 A1 EP2846002 A1 EP 2846002A1 EP 14150517 A EP14150517 A EP 14150517A EP 2846002 A1 EP2846002 A1 EP 2846002A1
Authority
EP
European Patent Office
Prior art keywords
housing
sealing ring
outer sealing
gas turbine
turbine according
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
EP14150517.2A
Other languages
German (de)
French (fr)
Other versions
EP2846002B1 (en
Inventor
Walter Gieg
Petra Kufner
Rudolf Stanka
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP14150517.2A priority Critical patent/EP2846002B1/en
Priority to US14/584,811 priority patent/US9416676B2/en
Publication of EP2846002A1 publication Critical patent/EP2846002A1/en
Application granted granted Critical
Publication of EP2846002B1 publication Critical patent/EP2846002B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • Y10T29/49233—Repairing, converting, servicing or salvaging
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/53—Means to assemble or disassemble
    • Y10T29/53983—Work-supported apparatus

Definitions

  • the present invention relates to a gas turbine having a housing, an outer sealing ring, which is releasably attachable to the housing, and a clamping element for radially clamping the outer sealing ring and the housing against each other.
  • the document proposes to arrange a radial flange of the sealing ring axially positively between the C-clip and the housing.
  • the C-clip is acted upon by the gas force in the flow direction and thus clamps the radial flange of the sealing ring against the housing.
  • An object of one embodiment of the present invention is to provide an improved gas turbine.
  • a gas turbine in particular an aircraft engine gas turbine, a housing, an outer sealing ring, which is detachably attachable to the housing, in particular fixed, and a clamping element for radially clamping the outer sealing ring and the housing against each other, the in one embodiment, the outer sealing ring and the housing radially braced against each other and so frictionally secured together.
  • An anti-rotation device for preventing rotation or positive limiting a relative movement in the circumferential direction between the housing and outer sealing ring has one or more in the circumferential direction of each other, preferably at least substantially equidistant, spaced housing grooves, which extend in an embodiment, at least substantially, in the axial direction.
  • the groove (s) may be radially open or closed radially, with radially outwardly open grooves advantageously can be advantageous manufacturing and / or assembly technology, radially outwardly closed grooves, however, can advantageously protect the rotation.
  • housing grooves in each case engage one or more radial flanges of the outer sealing ring and (twist) secure the housing and outer sealing ring in a form-fitting manner in the circumferential direction.
  • a radial tension or a frictional engagement between the housing and the outer sealing ring and thus wear can be reduced.
  • the one or more radial flanges are arranged with play in the axial direction in the housing or the grooves.
  • the one or more radial flanges may be arranged with play in the circumferential direction in the housing or the grooves.
  • the assembly can be simplified and / or manufacturing tolerances and / or thermal deformations can be compensated.
  • the housing groove (s) is / are open at the end side opposite to the throughflow direction.
  • the housing groove (s) opens or opens into a housing front side in the direction of flow or open in this.
  • the sealing ring can advantageously be pulled axially out of its mounting position out of the housing front or housing because its radial flange (e) need not be removed from a groove closed against the direction of flow For example, by initial tilting or the like.
  • an axial length of the housing groove (s) from a housing front side in the direction of flow is greater than an axial wall thickness of the radial flange or the radial flanges.
  • the outer sealing ring is divided or segmented into two or more ring segments.
  • advantageously the production, assembly and / or disassembly can be improved.
  • the clamping element is annular, ring-shaped in another embodiment.
  • the clamping element may be formed in several parts and two or more, over the circumference, in particular at least substantially equidistant, distributed ring segments, wherein the sum of the circumferential lengths of the ring segments of the circumferential length of rotation, but also, in particular, may be lower.
  • the clamping element may have one or more so-called C-clips.
  • the clamping element in one embodiment has a, in particular C- or U-shaped, cross-section with a radially outer limb, which is supported on an outer circumferential surface of the housing, and a radially inner limb, which is supported on an inner circumferential surface of the outer sealing ring element, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.
  • the gas turbine has a rotor which is arranged radially opposite the outer sealing ring element in the housing.
  • the rotor or the outer sealing ring element may in particular be a first, a gas inlet next or in the flow direction first rotor or a foremost, a gas inlet next or in the flow direction first outer sealing ring element.
  • the rotor or the outer-sealing-ring element may be the first of the high-pressure turbine or the low-pressure turbine.
  • the housing may be the housing of the high-pressure turbine or the low-pressure turbine.
  • Fig. 3 shows a part of a gas turbine according to Fig. 2 of the US 2007/0231132 A1 , to the description of which reference is made and the contents of which are incorporated in the present disclosure.
  • the gas turbine of Fig. 3 has a housing 1 'to which an outer sealing ring 2' is attached with a Honigwabendichtung.
  • a C-clip 3 ' clamps an annular Radial flange 20 'of the sealing ring axially positive fit against the housing.
  • the C-clip is acted upon by the gas force on a preceding vane 12 in the flow direction and thus clamps the radial flange of the sealing ring against the housing.
  • Fig. 1 shows in Fig. 3 corresponding representation of a section along the line II in Fig. 2 a portion of an aircraft engine gas turbine according to an embodiment of the present invention.
  • Fig. 2 shows a section along the line II-II in Fig. 1 , Corresponding elements are designated by the same reference numerals distinguished by an apostrophe.
  • This comprises a housing 1, an outer sealing ring 2, which is releasably secured to the housing, and a clamping element 3, which is the outer sealing ring and the housing radially (vertically in Fig. 1 ) clamped against each other and so frictionally secured together.
  • Housing 1 and outer sealing ring 2 have an anti-rotation with a plurality of circumferentially spaced apart housing grooves 10 which extend in the axial direction (horizontally in Fig. 1, 2 ). In the radial direction, the grooves are radially outward (top in FIG Fig. 1 ) open.
  • each housing groove 10 of the housing 1 engages in each case a radial flange 20 of the outer sealing ring 2, thus securing the housing and outer sealing ring in a form-fitting manner in the circumferential direction (vertically in FIG Fig. 2 ).
  • the radial flanges are arranged with play s a in the axial direction in the housing grooves.
  • the radial flanges also play in the circumferential direction to the housing grooves, which in Fig. 2 is recognizable.
  • the housing grooves are frontally opposite to the direction of flow (to the left in Fig. 1, 2 ) open.
  • the housing grooves opens or open into a housing front side 11 in the direction of flow.
  • the sealing ring 2 can advantageously be axially opposite Flow direction (to the left in Fig. 1, 2 ) from his in Fig. 1, 2 shown mounting position out of the housing end face 11 and the housing 1 are pulled out.
  • the axial length t 1 of the housing grooves 10 from the housing front side 11 in the direction of flow is greater than the axial wall thickness t 2 of the radial flanges 20.
  • the outer sealing ring is divided into several ring segments or segmented (not shown).
  • the clamping element is formed in several parts ring segment-shaped and has a plurality of distributed over the circumference ring segments in the form of C-clips. Accordingly, the clamping element has an in Fig. 1 recognizable C-shaped cross-section with a radially outer leg 31, which is supported on an outer peripheral surface of the housing 1, and a radially inner leg 32, which is supported on an inner peripheral surface of the outer sealing ring element 2, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.
  • the gas turbine has a first rotor 18 in the direction of flow (in FIG Fig. 1 not shown, cf. For this Fig. 3 ).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

Die vorliegende Erfindung betrifft eine Gasturbine mit einem Gehäuse (1), einem Außendichtring (2), der lösbar an dem Gehäuse befestigbar ist, einem Klemmelement (3) zum radialen Verspannen des Außendichtrings und des Gehäuses gegeneinander, und einer Verdrehsicherung, die wenigstens eine Gehäusenut (10) und einen Radialflansch (20) des Außendichtrings aufweist, der mit Spiel (S a ) in Axial- und/oder Umfangsrichtung formschlüssig in der Gehäusenut verdrehsicherbar ist.The present invention relates to a gas turbine with a housing (1), an outer sealing ring (2) which is releasably attachable to the housing, a clamping element (3) for radially clamping the outer sealing ring and the housing against each other, and a rotation, the at least one Gehäusenut (10) and a radial flange (20) of the outer sealing ring, which with clearance (S a) in the axial direction and / or circumferential direction positively in the housing groove against rotation is.

Description

Die vorliegende Erfindung betrifft eine Gasturbine mit einem Gehäuse, einem Außendichtring, der lösbar an dem Gehäuse befestigbar ist, und einem Klemmelement zum radialen Verspannen des Außendichtrings und des Gehäuses gegeneinander.The present invention relates to a gas turbine having a housing, an outer sealing ring, which is releasably attachable to the housing, and a clamping element for radially clamping the outer sealing ring and the housing against each other.

Aus der US 2007/0231132 A1 ist eine Gasturbine mit einem Gehäuse, einem Außendichtring, der lösbar an dem Gehäuse befestigt ist, und einem C-Clip bekannt, der den Außendichtring und das Gehäuse radial gegeneinander verspannt. Dadurch ist der Außendichtring in Umfangsrichtung reibschlüssig befestigt.From the US 2007/0231132 A1 is a gas turbine with a housing, an outer sealing ring, which is releasably secured to the housing, and a C-clip known which braces the outer sealing ring and the housing radially against each other. As a result, the outer sealing ring is frictionally secured in the circumferential direction.

Um vibrationsbedingte Mikrobewegungen in Axialrichtung zwischen Dichtring und Gehäuse zu vermeiden, schlägt die Druckschrift vor, einen Radialflansch des Dichtrings axial formschlüssig zwischen dem C-Clip und dem Gehäuse anzuordnen. Im Betrieb wird der C-Clip durch die Gaskraft in Durchströmungsrichtung beaufschlagt und klemmt so den Radialflansch des Dichtrings gegen das Gehäuse.In order to avoid vibration-induced micro-movements in the axial direction between the sealing ring and housing, the document proposes to arrange a radial flange of the sealing ring axially positively between the C-clip and the housing. In operation, the C-clip is acted upon by the gas force in the flow direction and thus clamps the radial flange of the sealing ring against the housing.

Bei Relativbewegungen, insbesondere infolge unterschiedlicher thermischer Deformationen, von Dichtring und Gehäuse übt diese Klemmung eine hohe Reibkraft aus, die zu entsprechend hohem Verschleiß führt.In relative movements, in particular as a result of different thermal deformations, of the sealing ring and housing this clamping exerts a high frictional force, which leads to correspondingly high wear.

Eine Aufgabe einer Ausführung der vorliegenden Erfindung ist es, eine verbesserte Gasturbine zur Verfügung zu stellen.An object of one embodiment of the present invention is to provide an improved gas turbine.

Diese Aufgabe wird durch die Merkmale des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen der Erfindung sind Gegenstand der Unteransprüche.This object is solved by the features of claim 1. Advantageous embodiments of the invention are the subject of the dependent claims.

Nach einem Aspekt der vorliegenden Erfindung weist eine Gasturbine, insbesondere eine Flugtriebwerk-Gasturbine, ein Gehäuse, einen Außendichtring, der lösbar an dem Gehäuse befestigbar, insbesondere befestigt, ist, und ein Klemmelement zum radialen Verspannen des Außendichtrings und des Gehäuses gegeneinander auf, das in einer Ausführung den Außendichtring und das Gehäuse radial gegeneinander verspannt und so reibschlüssig aneinander befestigt.According to one aspect of the present invention, a gas turbine, in particular an aircraft engine gas turbine, a housing, an outer sealing ring, which is detachably attachable to the housing, in particular fixed, and a clamping element for radially clamping the outer sealing ring and the housing against each other, the in one embodiment, the outer sealing ring and the housing radially braced against each other and so frictionally secured together.

Eine Verdrehsicherung zum Verdrehsichern bzw. formschlüssigen Begrenzen einer Relativbewegung in Umfangsrichtung zwischen Gehäuse und Außendichtring weist eine oder mehrere in Umfangsrichtung voneinander, vorzugsweise wenigstens im Wesentlichen äquidistant, beabstandete Gehäusenuten auf, die sich in einer Ausführung, wenigstens im Wesentlichen, in Axialrichtung erstrecken. In Radialrichtung können die Nut(en) radial außen offen oder geschlossen sein, wobei radial nach außen offene Nuten vorteilhafterweise fertigungs- und/oder montagetechnisch vorteilhaft sein können, radial außen geschlossene Nuten hingegen vorteilhafterweise die Verdrehsicherung schützen können.An anti-rotation device for preventing rotation or positive limiting a relative movement in the circumferential direction between the housing and outer sealing ring has one or more in the circumferential direction of each other, preferably at least substantially equidistant, spaced housing grooves, which extend in an embodiment, at least substantially, in the axial direction. In the radial direction, the groove (s) may be radially open or closed radially, with radially outwardly open grooves advantageously can be advantageous manufacturing and / or assembly technology, radially outwardly closed grooves, however, can advantageously protect the rotation.

In eine oder mehrere, vorzugsweise alle Gehäusenuten greifen jeweils ein oder mehrere Radialflansche des Außendichtrings ein und (verdreh)sichern so Gehäuse und Außendichtring formschlüssig in Umfangsrichtung. Hierdurch kann in einer Ausführung eine radiale Verspannung bzw. ein Reibschluss zwischen Gehäuse und Außendichtring und damit auch ein Verschleiß reduziert werden.In one or more, preferably all housing grooves in each case engage one or more radial flanges of the outer sealing ring and (twist) secure the housing and outer sealing ring in a form-fitting manner in the circumferential direction. As a result, in one embodiment, a radial tension or a frictional engagement between the housing and the outer sealing ring and thus wear can be reduced.

Nach einem Aspekt der vorliegenden Erfindung sind der oder die Radialflansche mit Spiel in Axialrichtung in der bzw. den Gehäusenuten angeordnet. Dadurch kann in einer Ausführung die einleitend erläuterte hohe axiale Klemmkraft infolge der Gaskraft im Betrieb reduziert, vorzugsweise vermieden und so ein Verschleiß reduziert werden.According to one aspect of the present invention, the one or more radial flanges are arranged with play in the axial direction in the housing or the grooves. As a result, in one embodiment, the initially explained high axial clamping force as a result of the gas force during operation can be reduced, preferably avoided, and so wear can be reduced.

Zusätzlich oder alternativ können der oder die Radialflansche mit Spiel in Umfangsrichtung in der bzw. den Gehäusenuten angeordnet sein. Dadurch können in einer Ausführung die Montage vereinfacht und/oder Fertigungstoleranzen und/oder thermische Deformationen kompensiert werden.Additionally or alternatively, the one or more radial flanges may be arranged with play in the circumferential direction in the housing or the grooves. As a result, in one embodiment, the assembly can be simplified and / or manufacturing tolerances and / or thermal deformations can be compensated.

Nach einem Aspekt der vorliegenden Erfindung ist bzw. sind die Gehäusenut(en) stirnseitig entgegen der Durchströmungsrichtung offen. Mit anderen Worten mündet bzw. münden die Gehäusenut(en) in eine in Durchströmungsrichtung vordere Gehäusestirnseite bzw. öffnen sich in diese. Hierdurch kann in einer Ausführung der Dichtring nach Entfernen des Klemmelements vorteilhaft axial entgegen der Durchströmungsrichtung aus seiner Montagelage heraus aus der Gehäusestirnseite bzw. dem Gehäuse herausgezogen werden, da sein(e) Radialflansch(e) nicht aus einer entgegen der Durchströmungsrichtung geschlossenen Nut entfernt werden müssen, beispielsweise durch anfängliches Kippen oder dergleichen.According to one aspect of the present invention, the housing groove (s) is / are open at the end side opposite to the throughflow direction. In other words, the housing groove (s) opens or opens into a housing front side in the direction of flow or open in this. As a result, in one embodiment, after removal of the clamping element, the sealing ring can advantageously be pulled axially out of its mounting position out of the housing front or housing because its radial flange (e) need not be removed from a groove closed against the direction of flow For example, by initial tilting or the like.

In einer Ausführung ist eine axiale Länge der Gehäusenut(en) von einer in Durchströmungsrichtung vorderen Gehäusestirnseite aus größer als eine axiale Wandstärke des Radialflanschs bzw. der Radialflansche. Hierdurch können die vorstehend erläuterten Aspekte der entgegen der Durchströmungsrichtung offenen Verdrehsicherung mit axialem Spiel vorteilhaft dargestellt werden. Unter einer axialen Länge wird vorliegend insbesondere die Länge eines Nutabschnitts in Axialrichtung verstanden, der sich von der Öffnung in der vorderen Gehäusestirnseite aus in Durchströmungsrichtung erstreckt und den Radialflansch aufnehmen kann, insbesondere also eine freie Weglänge des Radialflanschs in Durchströmungsrichtung.In one embodiment, an axial length of the housing groove (s) from a housing front side in the direction of flow is greater than an axial wall thickness of the radial flange or the radial flanges. As a result, the above-explained aspects of the anti-rotation device, which is open against the direction of flow, can be advantageously represented with axial play. In the present case, an axial length is understood to mean, in particular, the length of a groove section in the axial direction which extends from the opening in the front housing front side in the throughflow direction and can accommodate the radial flange, in particular a free path length of the radial flange in the direction of flow.

In einer Ausführung ist der Außendichtring in zwei oder mehr Ringsegmente geteilt bzw. segmentiert. Hierdurch kann in einer Ausführung vorteilhaft die Herstellung, Montage und/oder Demontage verbessert werden.In one embodiment, the outer sealing ring is divided or segmented into two or more ring segments. As a result, in one embodiment, advantageously the production, assembly and / or disassembly can be improved.

In einer Ausführung ist das Klemmelement ringförmig, in einer anderen Ausführung ringsegmentförmig. Insbesondere kann das Klemmelement mehrteilig ausgebildet sein und zwei oder mehr, über den Umfang, insbesondere wenigstens im Wesentlichen äquidistant, verteilte Ringsegmente aufweisen, wobei die Summe der Umfangslängen der Ringsegmente der Umfangslänge der Verdrehsicherung entsprechen, aber auch, insbesondere deutlich, geringer sein kann.In one embodiment, the clamping element is annular, ring-shaped in another embodiment. In particular, the clamping element may be formed in several parts and two or more, over the circumference, in particular at least substantially equidistant, distributed ring segments, wherein the sum of the circumferential lengths of the ring segments of the circumferential length of rotation, but also, in particular, may be lower.

Insbesondere kann das Klemmelement einen oder mehrere sogenannte C-Clipse aufweisen. Allgemein weist das Klemmelement in einer Ausführung einen, insbesondere C- oder U-förmigen, Querschnitt mit einem radial äußeren Schenkeln, der sich an einer Außenumfangsfläche des Gehäuses abstützt, und einem radial inneren Schenkeln auf, der sich an einer Innenumfangsfläche des Außendichtringelements abstützt, wobei der radial äußere Schenkel, der radial innere Schenkel und/oder eine Verbindung zwischen den beiden Schenkeln elastisch deformiert ist, um so Gehäuse und Außendichtring radial gegeneinander zu verspannen.In particular, the clamping element may have one or more so-called C-clips. In general, the clamping element in one embodiment has a, in particular C- or U-shaped, cross-section with a radially outer limb, which is supported on an outer circumferential surface of the housing, and a radially inner limb, which is supported on an inner circumferential surface of the outer sealing ring element, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.

In einer Ausführung weist die Gasturbine einen Rotor auf, der in dem Gehäuse dem Außendichtringelement radial gegenüber angeordnet ist. Der Rotor bzw. das Außendichtringelement kann insbesondere ein vorderster, einem Gaseintritt nächster bzw. in Durchströmungsrichtung erster Rotor bzw. ein vorderstes, einem Gaseintritt nächstes bzw. in Durchströmungsrichtung erstes Außendichtringelement sein. Wenn die Gasturbine eine Hochdruckturbine und eine dieser in Durchströmungsrichtung nachfolgende Niederdruckturbine aufweist, kann der Rotor bzw. das Außendichtringelement der bzw. das erste der Hochdruckturbine oder der Niederdruckturbine sein. Entsprechend kann das Gehäuse das Gehäuse der Hochdruckturbine oder der Niederdruckturbine sein.In one embodiment, the gas turbine has a rotor which is arranged radially opposite the outer sealing ring element in the housing. The rotor or the outer sealing ring element may in particular be a first, a gas inlet next or in the flow direction first rotor or a foremost, a gas inlet next or in the flow direction first outer sealing ring element. When the gas turbine has a high-pressure turbine and a low-pressure turbine downstream of it, the rotor or the outer-sealing-ring element may be the first of the high-pressure turbine or the low-pressure turbine. Accordingly, the housing may be the housing of the high-pressure turbine or the low-pressure turbine.

Weitere vorteilhafte Weiterbildungen der vorliegenden Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung bevorzugter Ausführungen. Hierzu zeigt, teilweise schematisiert:

Fig. 1
einen Teil einer Gasturbine in Fig. 3 entsprechender Darstellung nach einer Ausführung der vorliegenden Erfindung;
Fig. 2
einen Schnitt längs der Linie II-II in Fig. 1; und
Fig. 3
einen Teil einer Gasturbine nach dem Stand der Technik in einem Meridianschnitt.
Further advantageous developments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. This shows, partially schematized:
Fig. 1
a part of a gas turbine in Fig. 3 corresponding representation according to an embodiment of the present invention;
Fig. 2
a section along the line II-II in Fig. 1 ; and
Fig. 3
a part of a gas turbine according to the prior art in a meridian section.

Fig. 3 zeigt einen Teil einer Gasturbine gemäß Fig. 2 der US 2007/0231132 A1 , auf deren Beschreibung ergänzend Bezug genommen und deren Inhalt in die vorliegende Offenbarung einbezogen wird. Fig. 3 shows a part of a gas turbine according to Fig. 2 of the US 2007/0231132 A1 , to the description of which reference is made and the contents of which are incorporated in the present disclosure.

Die Gasturbine der Fig. 3 weist ein Gehäuse 1' auf, an dem ein Außendichtring 2' mit einer Honigwabendichtung befestigt ist. Hierzu klemmt ein C-Clip 3' einen ringförmigen Radialflansch 20' des Dichtrings axial formschlüssig gegen das Gehäuse. Im Betrieb wird der C-Clip durch die Gaskraft auf eine vorhergehende Leitschaufel 12 in Durchströmungsrichtung beaufschlagt und klemmt so den Radialflansch des Dichtrings gegen das Gehäuse.The gas turbine of Fig. 3 has a housing 1 'to which an outer sealing ring 2' is attached with a Honigwabendichtung. For this purpose, a C-clip 3 'clamps an annular Radial flange 20 'of the sealing ring axially positive fit against the housing. In operation, the C-clip is acted upon by the gas force on a preceding vane 12 in the flow direction and thus clamps the radial flange of the sealing ring against the housing.

Fig. 1 zeigt in Fig. 3 entsprechender Darstellung einen Schnitt längs der Linie I-I in Fig. 2 eines Teils einer Flugtriebwerk-Gasturbine nach einer Ausführung der vorliegenden Erfindung. Fig. 2 zeigt einen Schnitt längs der Linie II-II in Fig. 1. Einander entsprechende Elemente sind durch gleiche, durch einen Apostroph unterschiedene Bezugszeichen bezeichnet. Fig. 1 shows in Fig. 3 corresponding representation of a section along the line II in Fig. 2 a portion of an aircraft engine gas turbine according to an embodiment of the present invention. Fig. 2 shows a section along the line II-II in Fig. 1 , Corresponding elements are designated by the same reference numerals distinguished by an apostrophe.

Diese weist ein Gehäuse 1, einen Außendichtring 2, der lösbar an dem Gehäuse befestigt ist, und ein Klemmelement 3 auf, das den Außendichtring und das Gehäuse radial (vertikal in Fig. 1) gegeneinander verspannt und so reibschlüssig aneinander befestigt.This comprises a housing 1, an outer sealing ring 2, which is releasably secured to the housing, and a clamping element 3, which is the outer sealing ring and the housing radially (vertically in Fig. 1 ) clamped against each other and so frictionally secured together.

Gehäuse 1 und Außendichtring 2 weisen eine Verdrehsicherung mit mehreren in Umfangsrichtung voneinander beabstandeten Gehäusenuten 10 auf, die sich in Axialrichtung (horizontal in Fig. 1, 2) erstrecken. In Radialrichtung sind die Nuten radial außen (oben in Fig. 1) offen.Housing 1 and outer sealing ring 2 have an anti-rotation with a plurality of circumferentially spaced apart housing grooves 10 which extend in the axial direction (horizontally in Fig. 1, 2 ). In the radial direction, the grooves are radially outward (top in FIG Fig. 1 ) open.

In jede Gehäusenut 10 des Gehäuses 1 greift jeweils ein Radialflansch 20 des Außendichtrings 2 ein und sichert so Gehäuse und Außendichtring formschlüssig in Umfangsrichtung (vertikal in Fig. 2).In each housing groove 10 of the housing 1 engages in each case a radial flange 20 of the outer sealing ring 2, thus securing the housing and outer sealing ring in a form-fitting manner in the circumferential direction (vertically in FIG Fig. 2 ).

Die Radialflansche sind mit Spiel sa in Axialrichtung in den Gehäusenuten angeordnet. Zusätzlich weisen die Radialflansche auch Spiel in Umfangsrichtung zu den Gehäusenuten auf, welches in Fig. 2 erkennbar ist.The radial flanges are arranged with play s a in the axial direction in the housing grooves. In addition, the radial flanges also play in the circumferential direction to the housing grooves, which in Fig. 2 is recognizable.

Die Gehäusenuten sind stirnseitig entgegen der Durchströmungsrichtung (nach links in Fig. 1, 2) offen. Mit anderen Worten mündet bzw. münden die Gehäusenuten in eine in Durchströmungsrichtung vordere Gehäusestirnseite 11. Hierdurch kann der Dichtring 2 nach Entfernen des Klemmelements 3 vorteilhaft axial entgegen der Durchströmungsrichtung (nach links in Fig. 1, 2) aus seiner in Fig. 1, 2 dargestellten Montagelage heraus aus der Gehäusestirnseite 11 bzw. dem Gehäuse 1 herausgezogen werden.The housing grooves are frontally opposite to the direction of flow (to the left in Fig. 1, 2 ) open. In other words, the housing grooves opens or open into a housing front side 11 in the direction of flow. As a result, after removal of the clamping element 3, the sealing ring 2 can advantageously be axially opposite Flow direction (to the left in Fig. 1, 2 ) from his in Fig. 1, 2 shown mounting position out of the housing end face 11 and the housing 1 are pulled out.

Die axiale Länge t1 der Gehäusenuten 10 von der in Durchströmungsrichtung vorderen Gehäusestirnseite 11 aus ist größer als die axiale Wandstärke t2 der Radialflansche 20.The axial length t 1 of the housing grooves 10 from the housing front side 11 in the direction of flow is greater than the axial wall thickness t 2 of the radial flanges 20.

Der Außendichtring ist in mehrere Ringsegmente geteilt bzw. segmentiert (nicht dargestellt).The outer sealing ring is divided into several ring segments or segmented (not shown).

Das Klemmelement ist mehrteilig ringsegmentförmig ausgebildet und weist mehrere, über den Umfang verteilte Ringsegmente in Form von C-Clipsen auf. Entsprechend weist das Klemmelement einen in Fig. 1 erkennbaren C-förmigen Querschnitt mit einem radial äußeren Schenkeln 31, der sich an einer Außenumfangsfläche des Gehäuses 1 abstützt, und einem radial inneren Schenkeln 32 auf, der sich an einer Innenumfangsfläche des Außendichtringelements 2 abstützt, wobei der radial äußere Schenkel, der radial innere Schenkel und/oder eine Verbindung zwischen den beiden Schenkeln elastisch deformiert ist, um so Gehäuse und Außendichtring radial gegeneinander zu verspannen.The clamping element is formed in several parts ring segment-shaped and has a plurality of distributed over the circumference ring segments in the form of C-clips. Accordingly, the clamping element has an in Fig. 1 recognizable C-shaped cross-section with a radially outer leg 31, which is supported on an outer peripheral surface of the housing 1, and a radially inner leg 32, which is supported on an inner peripheral surface of the outer sealing ring element 2, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.

Die Gasturbine weist einen in Durchströmungsrichtung ersten Rotor 18 auf (in Fig. 1 nicht dargestellt, vgl. hierzu Fig. 3).The gas turbine has a first rotor 18 in the direction of flow (in FIG Fig. 1 not shown, cf. For this Fig. 3 ).

Obwohl in der vorhergehenden Beschreibung exemplarische Ausführungen erläutert wurden, sei darauf hingewiesen, dass eine Vielzahl von Abwandlungen möglich ist. Außerdem sei darauf hingewiesen, dass es sich bei den exemplarischen Ausführungen lediglich um Beispiele handelt, die den Schutzbereich, die Anwendungen und den Aufbau in keiner Weise einschränken sollen. Vielmehr wird dem Fachmann durch die vorausgehende Beschreibung ein Leitfaden für die Umsetzung von mindestens einer exemplarischen Ausführung gegeben, wobei diverse Änderungen, insbesondere in Hinblick auf die Funktion und Anordnung der beschriebenen Bestandteile, vorgenommen werden können, ohne den Schutzbereich zu verlassen, wie er sich aus den Ansprüchen und diesen äquivalenten Merkmalskombinationen ergibt.Although exemplary embodiments have been explained in the foregoing description, it should be understood that a variety of modifications are possible. It should also be noted that the exemplary embodiments are merely examples that are not intended to limit the scope, applications and construction in any way. Rather, by the foregoing description, the skilled person will be given a guideline for the implementation of at least one exemplary embodiment, wherein various changes, in particular with regard to the function and arrangement of the described components, can be made without departing from the scope of the invention as it results from the claims and these equivalent combinations of features.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1; 1'1; 1'
Gehäusecasing
1010
Gehäusenuthousing groove
1111
GehäusestirnseiteBody face
1212
Leitschaufelvane
1818
Rotorrotor
2; 2'2; 2 '
AußendichtringOuter sealing ring
20, 20'20, 20 '
Radialflanschradial flange
3; 3'3; 3 '
C-Clips (Klemmelement)C-clips (clamping element)
31; 31'31; 31 '
erster Schenkelfirst leg
32; 32'32; 32 '
zweiter Schenkelsecond leg

Claims (7)

Gasturbine mit einem Gehäuse (1), einem Außendichtring (2), der lösbar an dem Gehäuse befestigbar ist, und einem Klemmelement (3) zum radialen Verspannen des Außendichtrings und des Gehäuses gegeneinander, gekennzeichnet durch eine Verdrehsicherung, die wenigstens eine Gehäusenut (10) und einen Radialflansch (20) des Außendichtrings aufweist, der mit Spiel (sa) in Axial- und/oder Umfangsrichtung formschlüssig in der Gehäusenut verdrehsicherbar ist.Gas turbine with a housing (1), an outer sealing ring (2) which can be detachably fastened to the housing, and a clamping element (3) for radial clamping of the outer sealing ring and the housing relative to one another, characterized by an anti-rotation device which has at least one housing groove (10) and a radial flange (20) of the outer sealing ring, which with clearance (s a ) in the axial and / or circumferential direction positively in the housing groove against rotation is. Gasturbine nach Anspruch 1, dadurch gekennzeichnet, dass die Gehäusenut stirnseitig entgegen der Durchströmungsrichtung offen ist.Gas turbine according to claim 1, characterized in that the Gehäusenut frontally opposite to the flow direction is open. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass eine axiale Länge (t1) der Gehäusenut von einer in Durchströmungsrichtung vorderen Gehäusestirnseite (11) aus größer ist als eine axiale Wandstärke (t2) des Radialflanschs.Gas turbine according to one of the preceding claims, characterized in that an axial length (t 1 ) of the housing groove from a front in the flow direction housing end face (11) is greater than an axial wall thickness (t 2 ) of the radial flange. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Außendichtring segmentiert ist.Gas turbine according to one of the preceding claims, characterized in that the outer sealing ring is segmented. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Klemmelement ring- oder ringsegmentförmig ist.Gas turbine according to one of the preceding claims, characterized in that the clamping element is ring-shaped or ring-segment-shaped. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Klemmelement einen, insbesondere C- oder U-förmigen, Querschnitt mit zwei Schenkeln (31, 32) aufweist, von denen einer (31) sich an einer Außenumfangsfläche des Gehäuses und der andere (32) sich an einer Innenumfangsfläche des Außendichtringelements unter elastischer Deformation des Klemmringelements abstützt.Gas turbine according to one of the preceding claims, characterized in that the clamping element has a, in particular C- or U-shaped, cross-section with two legs (31, 32), one of which (31) on an outer peripheral surface of the housing and the other ( 32) is supported on an inner circumferential surface of the outer sealing ring element under elastic deformation of the clamping ring element. Gasturbine nach einem der vorhergehenden Ansprüche, gekennzeichnet durch einen, insbesondere in Durchströmungsrichtung ersten, Rotor (18), der in dem Gehäuse dem Außendichtringelement gegenüber angeordnet ist.Gas turbine according to one of the preceding claims, characterized by a first, in particular in the flow direction, the first rotor (18), which is arranged in the housing opposite the outer sealing ring element.
EP14150517.2A 2013-09-06 2014-01-09 Gas turbine Active EP2846002B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14150517.2A EP2846002B1 (en) 2013-09-06 2014-01-09 Gas turbine
US14/584,811 US9416676B2 (en) 2013-09-06 2014-12-29 Gas turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13183274.3A EP2846001B1 (en) 2013-09-06 2013-09-06 Assembly and disassembly methods of a rotor of a gas turbine and corresponding tool
EP14150517.2A EP2846002B1 (en) 2013-09-06 2014-01-09 Gas turbine

Publications (2)

Publication Number Publication Date
EP2846002A1 true EP2846002A1 (en) 2015-03-11
EP2846002B1 EP2846002B1 (en) 2019-11-20

Family

ID=49123719

Family Applications (3)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (en) 2013-09-06 2013-09-06 Assembly and disassembly methods of a rotor of a gas turbine and corresponding tool
EP14150517.2A Active EP2846002B1 (en) 2013-09-06 2014-01-09 Gas turbine
EP14150518.0A Active EP2846003B1 (en) 2013-09-06 2014-01-09 Gas turbine, corresponding assembly and disassembly methods of a rotor of a gas turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (en) 2013-09-06 2013-09-06 Assembly and disassembly methods of a rotor of a gas turbine and corresponding tool

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14150518.0A Active EP2846003B1 (en) 2013-09-06 2014-01-09 Gas turbine, corresponding assembly and disassembly methods of a rotor of a gas turbine

Country Status (3)

Country Link
US (5) US10125627B2 (en)
EP (3) EP2846001B1 (en)
ES (3) ES2935815T3 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2935815T3 (en) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Dis)assembly of a gas turbine rotor, in particular front
DE102013224199A1 (en) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gas turbine blade
US20170089213A1 (en) * 2015-09-28 2017-03-30 United Technologies Corporation Duct with additive manufactured seal
US10370996B2 (en) 2016-08-23 2019-08-06 United Technologies Corporation Floating, non-contact seal with offset build clearance for load imbalance
US10385715B2 (en) 2016-08-29 2019-08-20 United Technologies Corporation Floating, non-contact seal with angled beams
US10550708B2 (en) 2016-08-31 2020-02-04 United Technologies Corporation Floating, non-contact seal with at least three beams
DE102016222608A1 (en) 2016-11-17 2018-05-17 MTU Aero Engines AG Sealing arrangement for a guide vane arrangement of a gas turbine
JP6684698B2 (en) * 2016-12-12 2020-04-22 三菱重工エンジン＆ターボチャージャ株式会社 Turbocharger
US20190218928A1 (en) * 2018-01-17 2019-07-18 United Technologies Corporation Blade outer air seal for gas turbine engine
CN108533333B (en) * 2018-05-05 2023-10-13 宁波天生密封件有限公司 Steam turbine cannula sealing device and use method thereof
DE102018210601A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE
DE102018210600A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG COAT RING ARRANGEMENT FOR A FLOWING MACHINE
FR3083563B1 (en) * 2018-07-03 2020-07-24 Safran Aircraft Engines AIRCRAFT TURBOMACHINE SEALING MODULE
FR3092861B1 (en) * 2019-02-18 2023-02-10 Safran Aircraft Engines TURBOMACHINE ASSEMBLY INCLUDING A CLEAT ON A SEALING RING
IT201900014736A1 (en) * 2019-08-13 2021-02-13 Ge Avio Srl Integral sealing elements for blades held in a rotatable annular outer drum rotor in a turbomachinery.
CN113814915B (en) * 2020-06-18 2022-11-04 中国航发商用航空发动机有限责任公司 Fixing clamp, assembly component and assembly method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60122083T2 (en) * 2000-10-19 2007-03-01 Snecma Arrangement for connecting a stator ring to a support carrier
FR2891583A1 (en) * 2005-09-30 2007-04-06 Snecma Sa Low pressure turbine for jet engine of aircraft, has case mounted inside sealing sectors, where each sector comprises hook with end in form of axial annular stop extending radially towards exterior and supported against upstream end of rib
US20070231132A1 (en) 2006-03-30 2007-10-04 Snecma Device for attaching ring sectors to a turbine casing of a turbomachine

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2916874A (en) * 1957-01-31 1959-12-15 United Aircraft Corp Engine construction
US4053254A (en) 1976-03-26 1977-10-11 United Technologies Corporation Turbine case cooling system
US4650394A (en) 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US5267397A (en) * 1991-06-27 1993-12-07 Allied-Signal Inc. Gas turbine engine module assembly
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
US5639211A (en) * 1995-11-30 1997-06-17 United Technology Corporation Brush seal for stator of a gas turbine engine case
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
FR2780443B1 (en) * 1998-06-25 2000-08-04 Snecma HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
FR2800797B1 (en) * 1999-11-10 2001-12-07 Snecma ASSEMBLY OF A RING BORDING A TURBINE TO THE TURBINE STRUCTURE
US7186078B2 (en) 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US6942445B2 (en) * 2003-12-04 2005-09-13 Honeywell International Inc. Gas turbine cooled shroud assembly with hot gas ingestion suppression
US7147436B2 (en) * 2004-04-15 2006-12-12 United Technologies Corporation Turbine engine rotor retainer
FR2869944B1 (en) * 2004-05-04 2006-08-11 Snecma Moteurs Sa COOLING DEVICE FOR FIXED RING OF GAS TURBINE
FR2885168A1 (en) * 2005-04-27 2006-11-03 Snecma Moteurs Sa SEALING DEVICE FOR A TURBOMACHINE ENCLOSURE, AND AIRCRAFT ENGINE EQUIPPED WITH SAME
DE102006027237A1 (en) * 2005-06-14 2006-12-28 Alstom Technology Ltd. Steam turbine for a power plant has guide blade rows that are arranged on a single blade ring which is in turn arranged in the inner casing
US7438520B2 (en) * 2005-08-06 2008-10-21 General Electric Company Thermally compliant turbine shroud mounting assembly
FR2899274B1 (en) 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
FR2899281B1 (en) 2006-03-30 2012-08-10 Snecma DEVICE FOR COOLING A TURBINE HOUSING OF A TURBOMACHINE
US7819622B2 (en) * 2006-12-19 2010-10-26 United Technologies Corporation Method for securing a stator assembly
FR2921410B1 (en) * 2007-09-24 2010-03-12 Snecma RING SECTOR INTERLOCKING DEVICE ON A TURBOMACHINE HOUSING, COMPRISING MEANS FOR ITS PRETENSION
FR2922589B1 (en) * 2007-10-22 2009-12-04 Snecma CONTROL OF THE AUBES SET IN A HIGH-PRESSURE TURBINE TURBINE
FR2923528B1 (en) * 2007-11-13 2009-12-11 Snecma TURBINE OR COMPRESSOR STAGE OF A TURBOREACTOR
FR2923525B1 (en) * 2007-11-13 2009-12-18 Snecma SEALING A ROTOR RING IN A TURBINE FLOOR
FR2923527B1 (en) * 2007-11-13 2013-12-27 Snecma STAGE OF TURBINE OR COMPRESSOR, IN PARTICULAR TURBOMACHINE
FR2923526B1 (en) * 2007-11-13 2013-12-13 Snecma TURBINE OR TURBOMACHINE COMPRESSOR STAGE
FR2931195B1 (en) * 2008-05-16 2014-05-30 Snecma DISSYMMETRICAL MEMBER FOR LOCKING RING SECTIONS ON A TURBOMACHINE HOUSING
FR2931196B1 (en) * 2008-05-16 2010-06-18 Snecma RING SECTOR INTERLOCKING DEVICE ON A TURBOMACHINE CASE, COMPRISING RADIAL PASSAGES FOR ITS PRETENSION
RU2522264C2 (en) * 2009-03-09 2014-07-10 Снекма Turbine housing assembly
FR2954400B1 (en) * 2009-12-18 2012-03-09 Snecma TURBINE STAGE IN A TURBOMACHINE
US20110243725A1 (en) * 2010-03-31 2011-10-06 General Electric Company Turbine shroud mounting apparatus with anti-rotation feature
US8926270B2 (en) * 2010-12-17 2015-01-06 General Electric Company Low-ductility turbine shroud flowpath and mounting arrangement therefor
FR2978197B1 (en) * 2011-07-22 2015-12-25 Snecma TURBINE AND TURBINE TURBINE TURBINE DISPENSER HAVING SUCH A DISPENSER
ES2935815T3 (en) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Dis)assembly of a gas turbine rotor, in particular front

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60122083T2 (en) * 2000-10-19 2007-03-01 Snecma Arrangement for connecting a stator ring to a support carrier
FR2891583A1 (en) * 2005-09-30 2007-04-06 Snecma Sa Low pressure turbine for jet engine of aircraft, has case mounted inside sealing sectors, where each sector comprises hook with end in form of axial annular stop extending radially towards exterior and supported against upstream end of rib
US20070231132A1 (en) 2006-03-30 2007-10-04 Snecma Device for attaching ring sectors to a turbine casing of a turbomachine

Also Published As

Publication number Publication date
EP2846001A1 (en) 2015-03-11
USRE48320E1 (en) 2020-11-24
ES2935815T3 (en) 2023-03-10
EP2846001B1 (en) 2023-01-11
US20180347388A1 (en) 2018-12-06
US9416676B2 (en) 2016-08-16
EP2846003A1 (en) 2015-03-11
ES2752555T3 (en) 2020-04-06
EP2846002B1 (en) 2019-11-20
US20150192026A1 (en) 2015-07-09
US20150192028A1 (en) 2015-07-09
US11268398B2 (en) 2022-03-08
US9822657B2 (en) 2017-11-21
ES2762511T3 (en) 2020-05-25
US20150071769A1 (en) 2015-03-12
EP2846003B1 (en) 2019-10-16
US10125627B2 (en) 2018-11-13

Similar Documents

Publication Publication Date Title
EP2846002B1 (en) Gas turbine
DE10210866C5 (en) Guide vane mounting in a flow channel of an aircraft gas turbine
DE19507673C2 (en) Guide wheel for turbomachinery
EP3199758B1 (en) Rotor in blisk or bling structure of an aircraft engine
DE102014212155B4 (en) Bearing device for a shaft of a turbocharger device
EP2806107B1 (en) Split inner ring
DE102010060284A1 (en) Fuse spacer assembly for an airfoil mounting system for insertion in the circumferential direction
DE602005001231T2 (en) Locking means for gas turbine engines
EP2268902B1 (en) Strut for an intermediate turbine housing and intermediate turbine housing
DE102012100013A1 (en) Axial holding device for a turbine system
EP3091188B1 (en) Flow engine with a sealing arrangement
EP3181827B1 (en) Turbomachine component connection
EP3176386B1 (en) Inner shroud assembly, corresponding inner shroud, inner casing and turbomachine
EP2853784B1 (en) Brush sealing for a turbo engine
EP2707629B1 (en) Apparatus for sealing off a pump space of a rotary piston pump, and rotary piston pump having same
EP2808486A1 (en) Balancing component for a rotor blade arrangement
DE102016203567A1 (en) Multi-vane stage turbomachine and method of partially dismantling such a turbomachine
DE102012200539A1 (en) Shielding device for turbine housing of thermal gas turbine, has restriction element for limiting flow channel in sections between high pressure side and low pressure side of turbine housing, where bar is arranged in flow channel
EP2497183A2 (en) Electric machine
EP2881545B1 (en) Sealing element, sealing device and gas turbine engine
EP3350416B1 (en) Gas turbine with improved mounting of the inner housing
DE102016225604B4 (en) Sealing arrangement, rotor with such a sealing arrangement and gas turbine with such a rotor
DE102019124640A1 (en) VANIFULER SHEATHING ARRANGEMENT USING A PIN WITH AN EXTERNAL THREADED BOLT AND A NUT
DE102014219063A1 (en) Concentric component arrangement of a gas turbine
EP2725202A1 (en) Inner ring seal support arrangement for an adjustable stator blade assembly of a turbomachine

Legal Events

Date Code Title Description
17P Request for examination filed

Effective date: 20140109

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

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

R17P Request for examination filed (corrected)

Effective date: 20150813

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: 20190626

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

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: DE

Ref legal event code: R096

Ref document number: 502014013075

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1204430

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191215

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191120

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: 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: 20191120

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: 20191120

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: 20200220

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: 20200221

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: 20200220

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: 20191120

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: 20191120

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: 20191120

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2762511

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20200525

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

Ref country code: RS

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

Effective date: 20191120

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: 20200320

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: 20191120

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: 20191120

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

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: 20191120

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: 20191120

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: 20191120

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: 20191120

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: 20200412

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502014013075

Country of ref document: DE

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

Ref country code: SK

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

Effective date: 20191120

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: 20191120

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: 20191120

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200131

26N No opposition filed

Effective date: 20200821

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: 20200109

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

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: 20191120

Ref country code: LI

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

Effective date: 20200131

Ref country code: CH

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

Effective date: 20200131

Ref country code: BE

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

Effective date: 20200131

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: 20191120

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

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: 20191120

Ref country code: IE

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

Effective date: 20200109

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1204430

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200109

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: 20200109

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: 20191120

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: 20191120

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: 20191120

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: 20191120

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

Ref country code: ES

Payment date: 20240216

Year of fee payment: 11

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

Ref country code: DE

Payment date: 20240119

Year of fee payment: 11

Ref country code: GB

Payment date: 20240124

Year of fee payment: 11

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

Ref country code: FR

Payment date: 20240123

Year of fee payment: 11