EP1741875B1 - Circuits de refroidissement pour aube mobile de turbomachine - Google Patents

Circuits de refroidissement pour aube mobile de turbomachine Download PDF

Info

Publication number
EP1741875B1
EP1741875B1 EP06115023A EP06115023A EP1741875B1 EP 1741875 B1 EP1741875 B1 EP 1741875B1 EP 06115023 A EP06115023 A EP 06115023A EP 06115023 A EP06115023 A EP 06115023A EP 1741875 B1 EP1741875 B1 EP 1741875B1
Authority
EP
European Patent Office
Prior art keywords
blade
cavity
pressure
radial end
suction
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
EP06115023A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1741875A1 (fr
Inventor
Jacques Boury
Patrice Eneau
Sylvain Paquin
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1741875A1 publication Critical patent/EP1741875A1/fr
Application granted granted Critical
Publication of EP1741875B1 publication Critical patent/EP1741875B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to the general field of cooling turbomachine moving blades, and in particular to the blades of the high-pressure turbine.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a cooling circuit for a mobile blade that allows efficient cooling of the blade without degrading the blades. aerodynamic performance of the turbine and which has a low manufacturing cost.
  • the blade according to the invention comprises in its central part a lower pressure cooling circuit and an extrados cooling circuit.
  • the intrados cooling circuit comprises at least first and second intrados cavities extending radially and in the direction of the thickness of the blade from the intrados of the blade to a radially extending central wall and in the direction of the skeleton of the dawn, a central cavity extending radially and in the direction of the thickness of the blade from the intrados to the extrados of the dawn, an opening of air at a radial end of the first intrados cavity to supply air to the intrados circuit, a first passage communicating the other radial end of the first intrados cavity with a radial end adjacent to the second intrados cavity, a second passage communicating the other radial end of the second intrados cavity with a radial end adjacent to the central cavity, and outlet orifices opening into the central cavity and opening on the intrados face of the dawn .
  • the extrados cooling circuit comprises at least a first and a second extrados cavity extending radially and in the direction of the thickness of the blade from the extrados of the blade to the central wall, a central cavity extending radially and in the direction of the thickness of the blade from the intrados to the extrados of the blade, an air inlet opening at a radial end of the first cavity extrados for supplying air to the extrados circuit, a first passage communicating the other radial end of the first extrados cavity with a radial end adjacent to the second extrados cavity, a second passage communicating the other radial end of the second extrados cavity with a radial end close to the central cavity, and outlet orifices opening into the central cavity and opening on the intrados face of the blade.
  • the blade further comprises a cooling circuit leading edge comprising at least one cavity extending radially in the vicinity of the leading edge of the blade, at least one orifice of air inlet opening into the leading edge cavity and outlet openings opening into said leading edge cavity and opening on the leading edge of the blade.
  • the blade further comprises a trailing edge cooling circuit comprising at least one cavity extending radially in the vicinity of the trailing edge of the blade, at least one inlet orifice. air opening into the cavity trailing edge and outlet openings opening in said cavity trailing edge and opening on the intrados face of the blade.
  • the internal walls of the cavities of the intrados and extrados cooling circuits are provided with flow interferers intended to increase the heat transfer along these walls.
  • the Figures 1 to 3 represent a moving blade 10 of a turbomachine, such as a moving blade of a high-pressure turbine.
  • a turbomachine such as a moving blade of a high-pressure turbine.
  • the invention can also be applied to other blades turbomachine, for example the blades of the low-pressure turbine thereof.
  • the blade 10 comprises an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14.
  • This aerodynamic surface consists of a leading edge 16 disposed opposite the blade. flow of the hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite the leading edge 16, a lateral face 20 and an extrados lateral face 22, these lateral faces 20 , 22 connecting the leading edge 16 to the trailing edge 18.
  • the moving blade 10 of a turbomachine comprises in its central part C , that is to say in its part for which the distance between its intrados 20 and extrados faces 22 is the most important, a cooling circuit with a lower pressure and an extrados cooling circuit.
  • the intrados cooling circuit of the blade comprises in particular at least a first intrados cavity 24, a second intrados cavity 26 and a central cavity 28 (a larger number of intrados cavities is perfectly possible).
  • the cavities 24, 26 and 28 extend radially between the foot 12 and the top 14 of the blade.
  • the intrados cavities 24, 26 extend in the direction of the thickness of the blade (that is to say in the direction of its width defined between its faces intrados 20 and extrados 22) from the face intrados 20 of the blade to a wall (or partition) central 30 extending, firstly radially between the foot 12 and the top 14 of the blade, and secondly in the direction of the skeleton 32 of dawn.
  • the central cavity 28 it extends in the direction of the thickness of the blade from its intrados face 20 to its extrados face 22.
  • the intrados cooling circuit also comprises an air inlet opening 34 at a radial end of the first intrados cavity 24 (here at the foot 12 of the blade) to supply air to the intrados circuit.
  • a first passage 36 communicates the other radial end of the first intrados cavity 24 (that is to say at the top 14 of the blade) with a radial end adjacent to the second cavity intrados 26.
  • a second passage 38 does communicate the other radial end of the second intrados cavity 26 (that is to say at the root 12 of the blade) with a radial end adjacent to the central cavity 28 of the intrados circuit.
  • the intrados cooling circuit also has outlet orifices 40 opening in the central cavity 28 and opening on the intrados face 20 of the blade. These orifices 40 are regularly distributed over the entire radial height of the blade.
  • the circulation of the cooling air which runs through this intrados circuit follows clearly from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 34.
  • the air first passes through the first intrados cavity 24 and then the second intrados cavity 26 and finally the central cavity 28 before being emitted on the underside 20 of the dawn through the outlet ports 40.
  • the extrados cooling circuit of the blade comprises in particular at least a first extrados cavity 42, a second extrados cavity 44 and a central cavity 46 (a larger number of extrados cavities is perfectly possible).
  • the cavities 42, 44 and 46 extend radially between the foot 12 and the top 14 of the blade.
  • the extrados cavities 42, 44 extend in the direction of the thickness of the blade from the extrados face 22 of the blade to the central wall 30 defined above in connection with the cooling system intrados of dawn.
  • the central cavity 46 it extends in the direction of the thickness of the blade from its intrados face 20 to its extrados face 22.
  • the extrados cooling circuit also comprises an air intake opening 48 at a radial end of the first extrados cavity 42 (here at the foot 12 of the blade) to supply air to the extrados circuit.
  • a first passage 50 communicates the other radial end of the first extrados cavity 42 (that is to say at the top 14 of the blade) with a radial end adjacent to the second extrados cavity 44.
  • a second passage 52 communicates the other radial end of the second extrados cavity 44 (that is to say at the root 12 of the blade) with a radial end adjacent to the central cavity 46 of the extrados circuit.
  • the extrados cooling circuit also has outlet orifices 54 opening in the central cavity 46 and opening on the intrados face 20 of the blade. These orifices 54 are regularly distributed over the entire radial height of the blade.
  • the circulation of the cooling air which runs through this extrados circuit derives evidently from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 48.
  • the air firstly travels through the first extrados cavity 42 and then the second extrados cavity 44 and finally the central cavity 46 before being emitted on the underside 20 of the dawn through the outlets 54.
  • the inner and outer cooling circuits each have their own air inlet opening and that there is no air communication from one circuit to the other so that these circuits are completely independent of each other. one of the other.
  • intrados cavities 24, 26 and the extrados cavities 42, 44 of the intrados and extrados cooling circuits are disposed on either side of the central wall 30.
  • the central cavity 28 of the intrados circuit is located the side of the leading edge 16 of the blade, while the central cavity 46 of the extrados circuit is disposed on the side of the trailing edge 18 of the blade.
  • the internal walls of the cavities 24, 26, 28, 42, 44 and 46 of the suction and extrados cooling circuits may advantageously be provided with flow interferers 56 intended to increase heat transfer along these walls.
  • These flow disruptors may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade or in the form of pins or in any other equivalent form.
  • Additional cooling circuits make it possible to cool the leading edge 16 and the trailing edge 18 of the blade.
  • the leading edge cooling circuit comprises at least one cavity 58 extending radially in the vicinity of the leading edge 16 of the blade, at least one air inlet opening 60, 60 'opening in the leading edge cavity 58 and orifices of output 62 opening in the leading edge cavity and opening on the leading edge of the blade.
  • the trailing edge cooling circuit comprises at least one cavity 64 extending radially in the vicinity of the trailing edge 18 of the blade, at least one air intake orifice 66, 66 'opening into the cavity trailing edge 64 and outlets 68 opening in the cavity trailing edge and opening on the underside face 20 of the blade.
  • the leading edge cooling circuit comprises a central cavity 70 which extends radially between the root 12 and the top 14 of the blade and in the direction of the thickness of the blade from the lower surface 20 to the on the upper surface of dawn.
  • An air intake opening 72 is provided at a radial end of this central cavity 70 (here at the foot 12 of the blade).
  • the leading edge circuit also comprises a plurality of air intake orifices 60 distributed over the entire height of the blade. These orifices open into the central cavity 70 and open into the leading edge cavity 58.
  • the cooling air travels through the central cavity 70 and the leading edge cavity 58 before being emitted to the leading edge 16 of the blade through the outlet orifices 62.
  • the emission of air can also be performed on the underside 20 and on the extrados 22 of the dawn.
  • the trailing edge cooling circuit further comprises a central cavity 74 extending radially and in the direction of the thickness of the blade from the lower surface 20 to the extrados 22 of the blade and an opening 76 at a radial end of the central cavity 74 (here at the foot 12 of the blade) for supplying air to the circuit.
  • the circulation of air in this trailing edge cooling circuit is similar to that of the leading edge circuit: the air travels through the cavity central 74 and the cavity trailing edge 64 before being emitted on the underside face 20 of the blade at the trailing edge 18 of the latter.
  • the air intake port of the leading edge and trailing edge circuits of the blade 10 ' are openings at the respective radial end of the leading edge 58 and trailing edge 64 cavities (in FIG. the occurrence at the foot 12 of the dawn) and opening in the latter.
  • These air intake ports are not shown on the figure 4 but they are of the same type as those feeding the cooling circuits intrados and extrados of the dawn.
  • the cooling air therefore flows through the leading edge 58 and trailing edge 64 cavities of the foot 12 towards the apex 14 of the blade before being emitted by the respective outlet orifices 62, 68.
  • the blade leading edge cooling circuit 10 "has a plurality of air intake ports 60 'opening into the leading edge cavity 58 and opening into the central cavity 28 of the cooling circuit. Inlet cooling.
  • the blade trailing edge cooling circuit 10 "has a plurality of air intake orifices 66 'opening into the trailing edge cavity 64 and opening into the central cavity 46 of the cooling circuit. extrados cooling.
  • the cooling air supplying the leading edge and trailing edge circuits respectively comes from the intrados and extrados circuits of the blade.
  • the cooling circuits according to the invention have many advantages.
  • the presence of a central wall that is located along the skeleton in the central part of the blade and which is cooled by the air flowing through the intrados and extrados cavities of the intrados and extrados circuits allows to ensure an efficient and homogeneous cooling of the blade. This results in a significant drop in the average temperature of the dawn which has the effect of significantly increasing the life of the dawn and thus delay their replacement.
  • the aerodynamic performance of the turbine equipped with such blades are also not degraded by the presence of these cooling circuits.
  • the manufacture by molding of a blade provided with such cooling circuits does not pose any particular problem.
  • the cooling mode of the blades according to the invention also has the advantage of being able to easily adapt to so-called "high torque master” blades.
  • the master-couple of a dawn corresponds to the most important area of a circle inscribed in the cup of a dawn. Also, a dawn with a strong master-torque has a larger diameter circle than a standard master-torque dawn.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06115023A 2005-06-21 2006-06-06 Circuits de refroidissement pour aube mobile de turbomachine Active EP1741875B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0506266A FR2887287B1 (fr) 2005-06-21 2005-06-21 Circuits de refroidissement pour aube mobile de turbomachine

Publications (2)

Publication Number Publication Date
EP1741875A1 EP1741875A1 (fr) 2007-01-10
EP1741875B1 true EP1741875B1 (fr) 2008-09-17

Family

ID=35923394

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06115023A Active EP1741875B1 (fr) 2005-06-21 2006-06-06 Circuits de refroidissement pour aube mobile de turbomachine

Country Status (7)

Country Link
US (1) US7513739B2 (enExample)
EP (1) EP1741875B1 (enExample)
JP (1) JP4801513B2 (enExample)
CA (1) CA2550442C (enExample)
DE (1) DE602006002782D1 (enExample)
FR (1) FR2887287B1 (enExample)
RU (1) RU2403402C2 (enExample)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2893974B1 (fr) * 2005-11-28 2011-03-18 Snecma Circuit de refroidissement central pour aube mobile de turbomachine
US7296973B2 (en) * 2005-12-05 2007-11-20 General Electric Company Parallel serpentine cooled blade
US7862299B1 (en) * 2007-03-21 2011-01-04 Florida Turbine Technologies, Inc. Two piece hollow turbine blade with serpentine cooling circuits
US7985049B1 (en) * 2007-07-20 2011-07-26 Florida Turbine Technologies, Inc. Turbine blade with impingement cooling
WO2009016744A1 (ja) 2007-07-31 2009-02-05 Mitsubishi Heavy Industries, Ltd. タービン用翼
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
US9995148B2 (en) * 2012-10-04 2018-06-12 General Electric Company Method and apparatus for cooling gas turbine and rotor blades
JP5567180B1 (ja) * 2013-05-20 2014-08-06 川崎重工業株式会社 タービン翼の冷却構造
US9803500B2 (en) 2014-05-05 2017-10-31 United Technologies Corporation Gas turbine engine airfoil cooling passage configuration
US10012090B2 (en) * 2014-07-25 2018-07-03 United Technologies Corporation Airfoil cooling apparatus
EP3177810A1 (en) * 2014-08-07 2017-06-14 Siemens Aktiengesellschaft Turbine airfoil cooling system with bifurcated mid-chord cooling chamber
US11280214B2 (en) * 2014-10-20 2022-03-22 Raytheon Technologies Corporation Gas turbine engine component
FR3032173B1 (fr) 2015-01-29 2018-07-27 Safran Aircraft Engines Pale d'helice de turbopropulseur a soufflage
FR3067389B1 (fr) 2017-04-10 2021-10-29 Safran Aube de turbine presentant une structure amelioree
FR3067390B1 (fr) 2017-04-10 2019-11-29 Safran Aube de turbine presentant une structure amelioree
US10704398B2 (en) * 2017-10-03 2020-07-07 Raytheon Technologies Corporation Airfoil having internal hybrid cooling cavities
US10633980B2 (en) 2017-10-03 2020-04-28 United Technologies Coproration Airfoil having internal hybrid cooling cavities
US10626734B2 (en) 2017-10-03 2020-04-21 United Technologies Corporation Airfoil having internal hybrid cooling cavities
US10626733B2 (en) 2017-10-03 2020-04-21 United Technologies Corporation Airfoil having internal hybrid cooling cavities
US10815791B2 (en) * 2017-12-13 2020-10-27 Solar Turbines Incorporated Turbine blade cooling system with upper turning vane bank
FR3095834B1 (fr) * 2019-05-09 2021-06-04 Safran Aube de turbomachine à refroidissement amélioré
US11732594B2 (en) 2019-11-27 2023-08-22 General Electric Company Cooling assembly for a turbine assembly
FR3107920B1 (fr) 2020-03-03 2023-11-10 Safran Aircraft Engines Aube creuse de turbomachine et plateforme inter-aubes équipées de saillies perturbatrices de flux de refroidissement
CN113090335A (zh) * 2021-05-14 2021-07-09 中国航发湖南动力机械研究所 一种用于涡轮转子叶片的冲击加气膜双层壁冷却结构
KR20240140489A (ko) * 2023-03-17 2024-09-24 두산에너빌리티 주식회사 냉각 유로를 갖는 가스 터빈용 블레이드 및 그를 포함하는 가스 터빈

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06102963B2 (ja) * 1983-12-22 1994-12-14 株式会社東芝 ガスタ−ビン空冷翼
JPH0233843B2 (ja) * 1984-03-23 1990-07-31 Kogyo Gijutsuin Gasutaabindoyokunoreikyakukozo
SU1287678A2 (ru) * 1984-09-11 1997-02-20 О.С. Чернилевский Охлаждаемая лопатка турбины
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
FR2672338B1 (fr) * 1991-02-06 1993-04-16 Snecma Aube de turbine munie d'un systeme de refroidissement.
US5813835A (en) * 1991-08-19 1998-09-29 The United States Of America As Represented By The Secretary Of The Air Force Air-cooled turbine blade
US5356265A (en) * 1992-08-25 1994-10-18 General Electric Company Chordally bifurcated turbine blade
US5387085A (en) * 1994-01-07 1995-02-07 General Electric Company Turbine blade composite cooling circuit
SE512384C2 (sv) * 1998-05-25 2000-03-06 Abb Ab Komponent för en gasturbin
US6126396A (en) * 1998-12-09 2000-10-03 General Electric Company AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers
US6168381B1 (en) * 1999-06-29 2001-01-02 General Electric Company Airfoil isolated leading edge cooling
FR2829175B1 (fr) * 2001-08-28 2003-11-07 Snecma Moteurs Circuits de refroidissement pour aube de turbine a gaz
FR2829174B1 (fr) * 2001-08-28 2006-01-20 Snecma Moteurs Perfectionnement apportes aux circuits de refroidissement pour aube de turbine a gaz
FR2833298B1 (fr) * 2001-12-10 2004-08-06 Snecma Moteurs Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression
US6607356B2 (en) * 2002-01-11 2003-08-19 General Electric Company Crossover cooled airfoil trailing edge
EP1362982B1 (en) * 2002-05-09 2010-08-18 General Electric Company Turbine airfoil with single aft flowing three pass serpentine cooling circuit
US7097426B2 (en) * 2004-04-08 2006-08-29 General Electric Company Cascade impingement cooled airfoil
US7296972B2 (en) * 2005-12-02 2007-11-20 Siemens Power Generation, Inc. Turbine airfoil with counter-flow serpentine channels
US7296973B2 (en) * 2005-12-05 2007-11-20 General Electric Company Parallel serpentine cooled blade

Also Published As

Publication number Publication date
US7513739B2 (en) 2009-04-07
FR2887287B1 (fr) 2007-09-21
JP4801513B2 (ja) 2011-10-26
FR2887287A1 (fr) 2006-12-22
RU2403402C2 (ru) 2010-11-10
CA2550442A1 (fr) 2006-12-21
US20070116570A1 (en) 2007-05-24
RU2006122178A (ru) 2007-12-27
EP1741875A1 (fr) 2007-01-10
DE602006002782D1 (de) 2008-10-30
CA2550442C (fr) 2012-12-04
JP2007002843A (ja) 2007-01-11

Similar Documents

Publication Publication Date Title
EP1741875B1 (fr) Circuits de refroidissement pour aube mobile de turbomachine
EP0666406B1 (fr) Aube fixe ou mobile refroidie de turbine
EP1726783B1 (fr) Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire
EP1288438B1 (fr) Circuits de refroidissement pour aube de turbine à gaz
EP1288439B1 (fr) Circuit de refroidissement pour aube de turbine à gaz
EP2088286B1 (fr) Aube, roue à aube et turbomachine associées
CA2475083C (fr) Circuits de refroidissement pour aube de turbine a gaz
EP1790819B1 (fr) Aube mobile de turbomachine comprenant un circuit de refroidissement
EP3134620B1 (fr) Aube pour turbine de turbomachine comprenant un circuit de refroidissement à homogénéité améliorée
EP3519679B1 (fr) Aube de turbine comportant un circuit de refroidissement
EP1333155A1 (fr) Aube mobile de turbine haute pression munie d'un bord de fuite refroidi
EP4107369B1 (fr) Aube de turbine comportant trois types d'orifices de refroidissement du bord de fuite
CA2504168C (fr) Circuit de refroidissement a cavite a rapport de forme eleve pour aube de turbine a gaz
CA2569563C (fr) Aube de turbine a refroidissement et a duree de vie ameliores
EP3942158A1 (fr) Aube de turbomachine equipee d'un circuit de refroidissement optimise
EP3610132B1 (fr) Aube à circuit de refroidissement perfectionné
FR3111661A1 (fr) Aube de turbine avec système de refroidissement
WO2018215718A1 (fr) Aube pour turbine de turbomachine comprenant des cavites internes de circulation d'air de refroidissement

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: 20060606

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602006002782

Country of ref document: DE

Date of ref document: 20081030

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

26N No opposition filed

Effective date: 20090618

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006002782

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE GBR, DE

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006002782

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE EGBR, DE

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

Ref country code: DE

Payment date: 20250618

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20250625

Year of fee payment: 20

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

Ref country code: FR

Payment date: 20250620

Year of fee payment: 20

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

Ref country code: SE

Payment date: 20250618

Year of fee payment: 20