EP2464831B1 - Éléments de fixation d'aubes directrices dans une turbomachine - Google Patents

Éléments de fixation d'aubes directrices dans une turbomachine Download PDF

Info

Publication number
EP2464831B1
EP2464831B1 EP10760227.8A EP10760227A EP2464831B1 EP 2464831 B1 EP2464831 B1 EP 2464831B1 EP 10760227 A EP10760227 A EP 10760227A EP 2464831 B1 EP2464831 B1 EP 2464831B1
Authority
EP
European Patent Office
Prior art keywords
fastening element
housing
vane ring
turbomachine
absorbing
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.)
Not-in-force
Application number
EP10760227.8A
Other languages
German (de)
English (en)
Other versions
EP2464831A2 (fr
Inventor
Wilfried Weidmann
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
Publication of EP2464831A2 publication Critical patent/EP2464831A2/fr
Application granted granted Critical
Publication of EP2464831B1 publication Critical patent/EP2464831B1/fr
Not-in-force 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, with a housing and at least one vane ring, the outer shroud is divided by dividing lines into segments.
  • Such a turbomachine is for example from the DE 198 07 247 C2 known.
  • the vane rings are mounted in the region of their outer shroud with bearing pins on the housing of the turbomachine, wherein the segments of the vane ring are radially freely movable in the region of the outer shroud.
  • Such storage is also referred to as storage centering.
  • the bearing pin absorbs all transmitted from the vane ring on the housing forces, especially in the circumferential direction and axial direction.
  • Another turbomachine is out US2903237 known.
  • the invention has for its object to provide an improved attachment of a vane ring on the housing of the turbomachine, which allows a radial mobility of the vane ring segments while low load on the fasteners.
  • a turbomachine of the abovementioned type wherein the outer shroud of the vane ring is fastened to the housing via a first fastening element for axial force absorption and a second fastening element for circumferential force absorption independent of the first fastening element, and wherein the first and the second fastening element for the segments of the outer Shroud allow a game in the radial direction.
  • the fastening element for circumferential force absorption is formed by a substantially annular, radially inwardly projecting housing component, wherein first slots and / or first lugs are provided in the housing component, which project with second lugs or second slots in a radially outwardly projecting, Peripheral force-transmitting component of the outer shroud engage in such a way that the vane ring is fixed in the circumferential direction and the second nose or the second slot has a play in the radial direction.
  • This allows a simple geometry of the peripheral force transmitting components and thus the smallest possible space required.
  • fastening element for Axialkraftement arranged in the direction of force behind an axial force transmitting component of the outer shroud. This allows the transmission of compressive forces on the fastener.
  • the axial force is transmitted via a plurality of separate contact surfaces between the vane ring and the fastening element for Axialkraftfact. In this way, the friction between the axial force receiving fastener and the vane ring can be reduced.
  • the fastening element for Axialkraftment is annular and forms a positive connection with the housing. This allows, for example, a rotationally symmetrical embodiment of the fastener for Axialkraft technique.
  • the positive connection can be formed by a mounting extension on the housing and a groove in the annular fastener for Axialkraftment.
  • the inner radius of the mounting extension is greater than the outer radius of the outer shroud. This allows a mounting of the turbomachine in the axial direction.
  • a plurality of fastening elements are provided for axial force transmission, which are arranged in the direction of force in front of an axial force transmitting component of the vane ring. In this way, the axial force is transferred from the vane ring via tensile forces on the fasteners.
  • the fastening elements for axial force transmission are radially elastic elements. This ensures the mobility of the vane ring segments in the radial direction.
  • the fastening elements for Axialkraftübertragung can be positively secured to the housing and the vane ring.
  • the preferably positive connection between the fastening element for Axialkraftement and the housing may be secured by a fuse wire. In this way, unintentional release of the connection between the axial force-receiving fastener and the housing is prevented.
  • FIGS. 1 to 3 a turbomachine 10 with a vane ring 12 is shown.
  • This has an outer shroud 16, which is divided by parting lines in individual segments 14.
  • the segments 14 of the outer shroud 16 can move in the radial direction.
  • FIG. 2 shows a portion of the turbomachine 10 with two vane rings 12 and a blade 18.
  • the two vane rings 12 are connected by a honeycomb carrier 20.
  • FIG. 3 shows a vane ring 12 between two blades 18.
  • the vane ring. 12 and the associated honeycomb carrier 20 are mounted in a housing 22 of the turbomachine 10, wherein the (in FIG. 3 not shown) attachment for the segments 14 of the outer shroud 16 of the vane ring 12 allows clearance in the radial direction for memory-centered attachment.
  • the outer shroud 16 of the vane ring 12 can move in the radial direction between the radially inwardly and outwardly located positions shown with dashed lines.
  • the various vanes are preferably integrally connected.
  • FIG. 4 shows a first embodiment of the attachment of the vane ring 12 on the housing 22 of the turbomachine 10.
  • a fastening element 24 for circumferential force receiving is a substantially annular, radially inwardly projecting housing member 26 in which a plurality of slots are provided.
  • the vane ring 12 has a radially outwardly projecting component 28 in the region of the outer cover strip 16, which forms lugs which are positively connected to the slots in the housing member 26 and fix the vane ring 12 in the circumferential direction.
  • the housing member 26 has lugs which engage in slots in the component 28 of the vane ring 12, or that on both the housing member 26 and the component 28 of the vane ring 12 lugs and slots are provided which mutually engage in order to establish the positive connection.
  • a force acting on the vane ring 12 in the circumferential direction is transmitted from the component 28 via the interlocking lugs and slots on the housing member 26, which receives the circumferential force and thus fixes the vane ring 12 in the circumferential direction in the housing 22 of the turbomachine 10.
  • Axially acting forces are not absorbed by the fastener 24 for circumferential force absorption.
  • the circumferential force receiving member 24, taken by itself, permits movement of the vane ring 12 in one or both axial directions.
  • a fastening element 30 for axial force absorption is arranged in the force direction behind an axial force-transmitting component 32 of the vane ring 12.
  • the direction of the axial force has in the embodiment shown from left to right.
  • the axial force is transferred from the vane ring 12 via the axial force transmitting member 32 to the fastener 30 for axial force absorption as a compressive force.
  • the axial force transmitting member 32 has a plurality of separate contact surfaces 34, via which the axial force between the vane ring 12 and the fastening element 30 is transmitted to Axialkraftfact.
  • a segment 14 of the shroud 16 of the vane ring 12 is shown, which has a respective contact surface 34 at its ends lying in the circumferential direction.
  • the contact surface 34 extends over the entire circumference of the vane ring 12.
  • a special surface structure or a special coating, such as armor be provided to keep the friction between the vane ring 12 and the fastener 30 for Axialkraftsuit as low as possible.
  • the slotted for mounting on the circumference fastener 30 for Axialkraftage is annular and has a running at its outer radius in the circumferential direction groove with which it is positively connected to a mounting extension 36 which is formed on the housing 22.
  • the inner radius of the mounting extension 36 is greater than the outer radius of the vane ring 12. In this way, the guide vane ring 12 can be inserted during assembly of the turbomachine 10 in the axial direction in the closed housing 22.
  • the annular mounting member slotted for mounting on the circumference 30 is used for axial force on the mounting extension 36 of the housing 22, wherein the mounting extension 36 engages positively in the groove of the fastener 30.
  • the inner radius of the axial force receiving member 30 is smaller than the outer radius of the diaphragm ring 12.
  • the vane ring 12 contacts the contact surfaces 34 on the axial force receiving member 30 and the vane ring 12 is fixed in its axial position by the fastener 30.
  • the axial force transmitting member 32 is in the opposite direction of the axial force on the fastening element 24 for circumferential force absorption. In this way, the axial position of the vane ring 12 by the two fastening elements 24, 30 for recordssskraftment and Axialkraftwork exactly defined, the axial force acting during normal operation of the turbomachine due to their direction is taken only by the fastener 30 for Axialkraftment.
  • the two fastening elements 24, 30 for circumferential force absorption and Axialkraftaufhahme together form a guide for the components 28, 32 of the segment 14 of the outer shroud 16 of the vane ring 12, which allows movement of the segment 14 in the radial direction.
  • the positive connection between the fastening element 30 for Axialkraftness and the mounting extension 36 of the housing 22 is secured by a fuse wire 38. It is also possible that the fastening element 30 is secured directly to the housing 22 by the safety wire 38 for Axialkraftaufhahme.
  • FIG. 6 A second embodiment of the fastening element 30 for Axialkraftaufhahme is in FIG. 6 shown.
  • the fastening element 30 for Axialkraftness is arranged in this embodiment in the direction of force in front of an axial force transmitting member 32 of the vane ring 12, whereby tensile forces between the axial force transmitting member 32 and the fastener 30 can be transmitted to Axialkraftment.
  • One or more fastening elements 30 are provided for axial force absorption per segment 14 of the outer shroud of the vane ring 12.
  • the fasteners 30 are positively secured to the housing 22 and the vane ring 12.
  • On the housing 22, the positive connection with the fastening element 30 is secured by a locking wire 38.
  • the positive connection between the fastener 30 and the vane ring 12 is secured by a clamp 40, which may be part of the honeycomb support 20 or a separate part.
  • the fastening elements 30 for Axialkraftage are radially elastic elements.
  • the attached to the vane ring 12 end of the fastening element 30 for Axialkraftage can move along a circular path around the attached to the housing 22 end of the fastener 30, wherein at small angles, the movement is approximately linear, takes place in the radial direction.
  • fastening elements 30 for axial force absorption are completely separate components.
  • a plurality and in particular all fastening elements 30 may be connected to one another at the end fastened to the housing 22, whereby a substantially annular fastening element 30 is formed, with a plurality of radially elastic extensions which are fastened to the guide vane ring 12 at their respective ends.
  • the radially inwardly projecting housing part 26, which forms the fastening element 24 for circumferential force absorption, and the peripheral force transmitting component 28 of the vane ring 12 is similar in design and function to in FIG. 4 described embodiment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (4)

  1. Turbomachine (10), en particulier turbine à gaz, comprenant un boîtier (22) et une couronne d'aubes directrices (12) dont l'anneau de renforcement extérieur (16) est divisé en segments (14) par des joints de séparation, l'anneau de renforcement extérieur (16) étant fixé au boîtier (22) par le biais d'un premier élément de fixation (30) destiné à absorber une force axiale et par le biais d'un second élément de fixation (24), indépendant du premier élément de fixation (30), destiné à absorber une force circonférentielle et les premier et second éléments de fixation (24, 30) permettant aux segments (14) de l'anneau de renforcement extérieur (16) d'avoir du jeu dans la direction radiale, le premier élément de fixation (30) destiné à absorber une force axiale ayant une forme annulaire et formant avec le boîtier (22) une liaison par complémentarité de formes, la liaison par complémentarité de formes étant formée par un appendice de montage (36) au niveau du boîtier (22) et une rainure circonférentielle ménagée dans l'élément de fixation annulaire (30) destiné à absorber une force axiale, et l'élément de fixation (30) destiné à absorber une force axiale étant disposé en arrière d'un composant de transmission de force axiale (32) de l'anneau de renforcement extérieur (16) par référence à la direction des forces, caractérisée en ce que la force axiale est transmise par une pluralité de surfaces de contact (34), séparées les unes des autres, entre la couronne d'aubes directrices (12) et l'élément de fixation (30) destiné à absorber une force axiale.
  2. Turbomachine (10) selon la revendication 1, caractérisée en ce que le second élément de fixation (24) destiné à absorber une force circonférentielle est formé par un composant de boîtier (26) de forme sensiblement annulaire et saillant radialement vers l'intérieur, des premières fentes et/ou des premiers ergots étant prévus dans le composant de boîtier (26), qui s'engagent avec des deuxièmes ergots ou des deuxièmes fentes d'un composant (28), saillant radialement vers l'extérieur et transmettant une force circonférentielle, de l'anneau de renforcement extérieur (16) de telle sorte que la couronne d'aubes directrices (12) soit fixée dans la direction circonférentielle et le deuxième ergot ou la deuxième fente présente du jeu dans la direction radiale.
  3. Turbomachine (10) selon la revendication 1, caractérisée en ce que le rayon intérieur de l'appendice de montage (36) est supérieur au rayon extérieur de l'anneau de renforcement extérieur (16).
  4. Turbomachine (10) selon l'une des revendications précédentes, caractérisée en ce que la liaison par complémentarité de formes entre l'élément de fixation (30) destiné à absorber une force axiale et le boîtier (22) est assurée par un fil de sécurité.
EP10760227.8A 2009-08-14 2010-08-05 Éléments de fixation d'aubes directrices dans une turbomachine Not-in-force EP2464831B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009037620A DE102009037620A1 (de) 2009-08-14 2009-08-14 Strömungsmaschine
PCT/DE2010/000927 WO2011018072A2 (fr) 2009-08-14 2010-08-05 Turbomachine

Publications (2)

Publication Number Publication Date
EP2464831A2 EP2464831A2 (fr) 2012-06-20
EP2464831B1 true EP2464831B1 (fr) 2018-04-25

Family

ID=43448339

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10760227.8A Not-in-force EP2464831B1 (fr) 2009-08-14 2010-08-05 Éléments de fixation d'aubes directrices dans une turbomachine

Country Status (5)

Country Link
US (1) US20120141253A1 (fr)
EP (1) EP2464831B1 (fr)
DE (1) DE102009037620A1 (fr)
ES (1) ES2669120T3 (fr)
WO (1) WO2011018072A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984428B1 (fr) * 2011-12-19 2018-12-07 Safran Aircraft Engines Redresseur de compresseur pour turbomachine.
ES2704485T3 (es) 2012-10-30 2019-03-18 MTU Aero Engines AG Fijación de soporte de junta para una turbomáquina
FR3009740B1 (fr) * 2013-08-13 2017-12-15 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
EP2937517B1 (fr) * 2014-04-24 2019-03-06 Safran Aero Boosters SA Stator de turbomachine axiale et turbomachine associée
DE102015202070A1 (de) 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
USD871468S1 (en) * 2017-03-28 2019-12-31 General Electric Company Flow ingestion discourager with ridged pattern for a turbomachine shroud

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE543281A (fr) * 1954-12-16
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3443791A (en) * 1966-11-23 1969-05-13 United Aircraft Corp Turbine vane assembly
GB1385666A (en) * 1973-07-06 1975-02-26 Rolls Royce Sealing of vaned assemblies of gas turbine engines
US4314793A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Temperature actuated turbine seal
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
IT1167241B (it) * 1983-10-03 1987-05-13 Nuovo Pignone Spa Sistema perfezionato per il fissaggio degli ugelli statorici alla cassa di una turbina di potenza
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US4957412A (en) * 1988-09-06 1990-09-18 Westinghouse Electric Corp. Apparatus and method for supporting the torque load on a gas turbine vane
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
DE19507673C2 (de) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Leitrad für Turbomaschinen
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
DE19807247C2 (de) * 1998-02-20 2000-04-20 Mtu Muenchen Gmbh Strömungsmaschine mit Rotor und Stator
DE50112597D1 (de) * 2001-04-12 2007-07-19 Siemens Ag Gasturbine mit axial verschiebbaren Gehäuseteilen
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6916154B2 (en) * 2003-04-29 2005-07-12 Pratt & Whitney Canada Corp. Diametrically energized piston ring
DE10359730A1 (de) * 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
US7144218B2 (en) * 2004-04-19 2006-12-05 United Technologies Corporation Anti-rotation lock
US7094026B2 (en) * 2004-04-29 2006-08-22 General Electric Company System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor
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
US7819622B2 (en) * 2006-12-19 2010-10-26 United Technologies Corporation Method for securing a stator assembly

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
WO2011018072A3 (fr) 2011-09-15
WO2011018072A2 (fr) 2011-02-17
ES2669120T3 (es) 2018-05-24
US20120141253A1 (en) 2012-06-07
EP2464831A2 (fr) 2012-06-20
DE102009037620A1 (de) 2011-02-17

Similar Documents

Publication Publication Date Title
EP2464831B1 (fr) Éléments de fixation d'aubes directrices dans une turbomachine
EP1728002B1 (fr) Elements intermediaires pour une combinaison disque de frein/moyeu et combinaison disque de frein/moyeu
EP1584793B1 (fr) Dispositif pour la fixation axiale d'aubes de turbine
EP1922471A1 (fr) Systeme de retenue axiale de d'aubes mobiles dans un rotor et utilisation dudit systeme
EP1989467B1 (fr) Ensemble roue dentée
EP2218873A1 (fr) Section de rotor pour un rotor d'une turbomachine, aube directrice pour une turbomachine et élément de blocage
DE102009028517B4 (de) Befestigungsanordnung von Planetenradbolzen
EP2806107B1 (fr) Bague intérieure séparée
EP1728972B1 (fr) Dispositif de verrouillage d'une aube de turbine
DE69913625T2 (de) Gasturbine
DE102011003419A1 (de) Ringförmiger Wälzlagerkäfig
EP1524409B1 (fr) Dispositif de verrouillage d'aube
EP2591253B1 (fr) Fourchette de sélection et procédé de production de ladite fourchette
DE102007035829A1 (de) Bremsscheibe
WO2018036818A1 (fr) Rotor muni d'une bague d'étanchéité segmentée
DE102008028371B4 (de) Toleranzring
DE102013211476A1 (de) Loslagersystem für eine elektrische Maschine
DE102006034985B4 (de) Verbindungsanordnung zwischen Hohlwellen und Gelenkinnenteil am Wellenende
EP3788236B1 (fr) Rotor pourvu d'une pièce disposée entre deux disques de rotor
EP1757830A2 (fr) Arrangement avec au moins deux anneaux synchronisateurs d'un dispositif de synchronisation
WO2017174723A1 (fr) Disque de rotor muni d'un élément d'étanchéité côté frontal
DE102009048905A1 (de) Verstellbare Axialkolbenmaschine mit einer Lagerschale für die Schwenkwiege
EP3521561A1 (fr) Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
DE102018113717B4 (de) Kupplungseinrichtung
DE102012209103B4 (de) Torsionsschwingungsdämpfer

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20120116

AK Designated contracting states

Kind code of ref document: A2

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

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

17Q First examination report despatched

Effective date: 20160517

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502010014924

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0025240000

Ipc: F01D0005220000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/22 20060101AFI20180206BHEP

Ipc: F01D 25/24 20060101ALI20180206BHEP

Ipc: F01D 9/04 20060101ALI20180206BHEP

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

INTG Intention to grant announced

Effective date: 20180301

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 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: AT

Ref legal event code: REF

Ref document number: 993146

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180515

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: 502010014924

Country of ref document: DE

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2669120

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20180524

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180425

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: 20180425

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: 20180425

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: 20180725

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: 20180425

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: 20180725

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: 20180425

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: 20180425

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

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: 20180425

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: 20180425

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: 20180726

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

Ref country code: PT

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

Effective date: 20180827

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010014924

Country of ref document: DE

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: 20180425

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: 20180425

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: 20180425

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: 20180425

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: 20180425

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

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: 20180425

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: 20180425

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

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

Ref country code: 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: 20180425

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20190128

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

Ref country code: LI

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

Effective date: 20180831

Ref country code: CH

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

Effective date: 20180831

Ref country code: LU

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

Effective date: 20180805

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180831

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: SI

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

Effective date: 20180425

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

Ref country code: IE

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

Effective date: 20180805

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

Ref country code: BE

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

Effective date: 20180831

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 993146

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180805

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

Ref country code: DE

Payment date: 20190822

Year of fee payment: 10

Ref country code: ES

Payment date: 20190919

Year of fee payment: 10

Ref country code: FR

Payment date: 20190822

Year of fee payment: 10

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: 20180425

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: 20180805

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

Ref country code: GB

Payment date: 20190827

Year of fee payment: 10

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

Ref country code: MT

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

Effective date: 20180425

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: 20180425

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

Ref country code: HU

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

Effective date: 20100805

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 NON-PAYMENT OF DUE FEES

Effective date: 20180425

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: 20180425

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

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: 20180825

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502010014924

Country of ref document: DE

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

Effective date: 20200805

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

Ref country code: DE

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

Effective date: 20210302

Ref country code: FR

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

Effective date: 20200831

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

Ref country code: GB

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

Effective date: 20200805

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20220110

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

Ref country code: ES

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

Effective date: 20200806