+

EP2846002B1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

Info

Publication number
EP2846002B1
EP2846002B1 EP14150517.2A EP14150517A EP2846002B1 EP 2846002 B1 EP2846002 B1 EP 2846002B1 EP 14150517 A EP14150517 A EP 14150517A EP 2846002 B1 EP2846002 B1 EP 2846002B1
Authority
EP
European Patent Office
Prior art keywords
housing
sealing ring
gas turbine
outer sealing
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.)
Active
Application number
EP14150517.2A
Other languages
German (de)
English (en)
Other versions
EP2846002A1 (fr
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/fr
Priority to US14/584,811 priority patent/US9416676B2/en
Publication of EP2846002A1 publication Critical patent/EP2846002A1/fr
Application granted granted Critical
Publication of EP2846002B1 publication Critical patent/EP2846002B1/fr
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 fastened to the housing fastened, in particular fastened, and a clamping element for radially clamping the outer sealing ring and the housing against each other, which in a version of the outer sealing ring and the housing clamped radially 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 can 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) open or open into a front side of the housing in the direction of flow or open into it.
  • 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 can be designed in several parts and have two or more, over the circumference, in particular at least substantially equidistantly, distributed ring segments, wherein the sum of the circumferential lengths the ring segments correspond to the circumferential length of the 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 limbs, which is supported on an outer peripheral surface of the housing, and a radially inner legs, which is supported on an inner peripheral surface of the outer sealing ring element 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 ,
  • 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 clamps a C-clip 3 '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 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 open or open into a housing front side 11 in the direction of flow.
  • the sealing ring 2 can advantageously be axially opposite to the throughflow direction (to the left in FIG 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)

Claims (8)

  1. Turbine à gaz comportant un boîtier (1), une bague d'étanchéité externe (2), pouvant être fixée de manière amovible au boîtier (1), et un élément de serrage (3) pour serrer radialement la bague d'étanchéité externe (2) et le boîtier (1) l'un contre l'autre, caractérisé en ce qu'un dispositif anti-rotation, qui présente au moins une gorge de boîtier (10) et une bride radiale (20) de la bague d'étanchéité extérieure (2), qui avec du jeu (sa) dans le sens axial dans la gorge de boîtier (10) peut empêcher toute rotation de par sa forme.
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que la gorge du boîtier (10) est ouverte du côté opposé frontalement au sens de l'écoulement.
  3. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce qu'une longueur axiale (t1) de la gorge de boîtier (10) d'une face avant finale du boîtier (11) selon la direction d'écoulement est supérieure à une épaisseur de paroi axiale (t2) de la bride radiale (20).
  4. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que la bague d'étanchéité externe (2) est segmentée.
  5. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que l'élément de serrage (3) est en forme d'anneau ou de segment d'anneau.
  6. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que l'élément de serrage (3) présente une section transversale, notamment en forme de C ou de U, avec deux jambes (31, 32), dont l'une (31) repose sur une surface périphérique extérieure du boîtier (1) et l'autre (32) repose sur une surface périphérique interne de la bague d'étanchéité externe (2) sous déformation élastique de l'élément de serrage (3).
  7. Turbine à gaz selon l'une des revendications précédentes, caractérisée par un, notamment dans le sens de l'écoulement premier, rotor (18), qui est disposé dans le boîtier (1) en regard de la bague d'étanchéité extérieure (2).
  8. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que la bride radiale (20) avec du jeu dans le sens circonférentiel dans la gorge de boîtier (10) peut empêcher toute rotation de par sa forme.
EP14150517.2A 2013-09-06 2014-01-09 Turbine à gaz Active EP2846002B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14150517.2A EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz
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 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150517.2A EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz

Publications (2)

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

Family

ID=49123719

Family Applications (3)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150517.2A Active EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz
EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz

Country Status (3)

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

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2935815T3 (es) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Des)montaje de un rotor de una turbina de gas, en particular delantero
DE102013224199A1 (de) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
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 (de) 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
JP6684698B2 (ja) * 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 ターボチャージャ
US20190218928A1 (en) * 2018-01-17 2019-07-18 United Technologies Corporation Blade outer air seal for gas turbine engine
CN108533333B (zh) * 2018-05-05 2023-10-13 宁波天生密封件有限公司 一种汽轮机插管密封装置及其使用方法
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
FR3083563B1 (fr) * 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef
FR3092861B1 (fr) * 2019-02-18 2023-02-10 Safran Aircraft Engines Ensemble de turbomachine comportant un taquet sur un jonc d'etancheite
IT201900014736A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
CN113814915B (zh) * 2020-06-18 2022-11-04 中国航发商用航空发动机有限责任公司 固定夹具、装配组件及组装方法
CN118848880B (zh) * 2024-09-26 2025-01-24 成都中科翼能科技有限公司 一种低压涡轮转子的篦齿封严环的拆卸工装及拆卸方法

Family Cites Families (37)

* 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 (fr) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc Assemblage d'un rotor à aubes et de son carter
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
FR2800797B1 (fr) * 1999-11-10 2001-12-07 Snecma Assemblage d'un anneau bordant une turbine a la structure de turbine
FR2815668B1 (fr) * 2000-10-19 2003-01-10 Snecma Moteurs Agencement de liaison d'un anneau de stator de turbine a une entretoise de support
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 (fr) * 2004-05-04 2006-08-11 Snecma Moteurs Sa Dispositif de refroidissement pour anneau fixe de turbine a gaz
FR2885168A1 (fr) * 2005-04-27 2006-11-03 Snecma Moteurs Sa Dispositif d'etancheite pour une enceinte d'une turbomachine, et moteur d'aeronef equipe de celui-ci
DE102006027237A1 (de) * 2005-06-14 2006-12-28 Alstom Technology Ltd. Dampfturbine
US7438520B2 (en) * 2005-08-06 2008-10-21 General Electric Company Thermally compliant turbine shroud mounting assembly
FR2891583B1 (fr) * 2005-09-30 2010-06-18 Snecma Turbine comportant des secteurs d'etancheite demontables par l'amont
FR2899281B1 (fr) 2006-03-30 2012-08-10 Snecma Dispositif de refroidissement d'un carter de turbine d'une turbomachine
FR2899275A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine
FR2899274B1 (fr) 2006-03-30 2012-08-17 Snecma Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
US7819622B2 (en) * 2006-12-19 2010-10-26 United Technologies Corporation Method for securing a stator assembly
FR2921410B1 (fr) * 2007-09-24 2010-03-12 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension
FR2922589B1 (fr) * 2007-10-22 2009-12-04 Snecma Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
FR2923527B1 (fr) * 2007-11-13 2013-12-27 Snecma Etage de turbine ou de compresseur, en particulier de turbomachine
FR2923525B1 (fr) * 2007-11-13 2009-12-18 Snecma Etancheite d'un anneau de rotor dans un etage de turbine
FR2923528B1 (fr) * 2007-11-13 2009-12-11 Snecma Etage de turbine ou de compresseur d'un turboreacteur
FR2923526B1 (fr) * 2007-11-13 2013-12-13 Snecma Etage de turbine ou de compresseur de turbomachine
FR2931196B1 (fr) * 2008-05-16 2010-06-18 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages radiaux permettant sa prehension
FR2931195B1 (fr) * 2008-05-16 2014-05-30 Snecma Organe dissymetrique de verrouillage de secteurs d'anneau sur un carter de turbomachine
WO2010103213A1 (fr) * 2009-03-09 2010-09-16 Snecma Ensemble d'anneau de turbine
FR2954400B1 (fr) * 2009-12-18 2012-03-09 Snecma Etage de turbine dans une 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 (fr) * 2011-07-22 2015-12-25 Snecma Distributeur de turbine de turbomachine et turbine comportant un tel distributeur
ES2935815T3 (es) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Des)montaje de un rotor de una turbina de gas, en particular delantero

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
US11268398B2 (en) 2022-03-08
US20150192026A1 (en) 2015-07-09
US20180347388A1 (en) 2018-12-06
US20150192028A1 (en) 2015-07-09
EP2846001A1 (fr) 2015-03-11
EP2846003A1 (fr) 2015-03-11
US10125627B2 (en) 2018-11-13
EP2846001B1 (fr) 2023-01-11
ES2762511T3 (es) 2020-05-25
US9822657B2 (en) 2017-11-21
EP2846003B1 (fr) 2019-10-16
ES2935815T3 (es) 2023-03-10
US9416676B2 (en) 2016-08-16
USRE48320E1 (en) 2020-11-24
ES2752555T3 (es) 2020-04-06
US20150071769A1 (en) 2015-03-12
EP2846002A1 (fr) 2015-03-11

Similar Documents

Publication Publication Date Title
EP2846002B1 (fr) Turbine à gaz
EP2960438B1 (fr) Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système
DE10210866C5 (de) Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine
DE19507673C2 (de) Leitrad für Turbomaschinen
EP3040560B1 (fr) Dispositif de boitier pour un etage d'un compresseur a plusieurs etages et procede de fabrication d'un dispositif de boitier
WO2007028703A1 (fr) Systeme de retenue axiale de d'aubes mobiles dans un rotor et utilisation dudit systeme
EP2806107B1 (fr) Bague intérieure séparée
DE102010060284A1 (de) Sicherungs-Abstandshalteranordnung für ein Schaufelblattbefestigungssystem zur Einführung in Umfangsrichtung
EP2268902B1 (fr) Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine
EP3287611A1 (fr) Turbine à gaz et procédé de suspension d'un segment d'aube de guidage d'une turbine à gaz
EP3091188B1 (fr) Turbomachine dotée d'un dispositif d'étanchéité
EP2871325A1 (fr) Virole interne d'une turbomachine et distributeur
EP3390784B1 (fr) Turbomachine à plusieurs étages d'aubes directrices et procédé pour démonter en partie une telle turbomachine
EP3176386B1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
DE102018206652B4 (de) Wartungsfreundliche Gleitringdichtung
EP2853784B1 (fr) Joint à brosse pour une turbomachine
DE602005001231T2 (de) Verriegelungsmittel für Gasturbinentriebwerke
EP2707629B1 (fr) Dispositif d'étanchéification d'une chambre de pompage d'une pompe à piston tournant, et pompe à piston tournant dotée de ce dispositif
EP2808486A1 (fr) Corps d'équilibrage pour un agencement d'aube directrice
EP2816198B1 (fr) Ensemble d'aube directrice, aube directrice et procédé de montage d'une aube directrice
WO2011054351A2 (fr) Machine électrique
EP2881545B1 (fr) Élément d'étanchéité, dispositif d'étanchéité et turbomachine
EP3536913B1 (fr) Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure
EP3350416B1 (fr) Turbine à gaz munie d'un support amélioré du carter intérieur
DE102010034569A1 (de) Leitschaufelträgerfixierung

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

点击 这是indexloc提供的php浏览器服务，不要输入任何密码和下载