EP1965024A1 - Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks - Google Patents

Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks Download PDF

Info

Publication number
EP1965024A1
EP1965024A1 EP08102089A EP08102089A EP1965024A1 EP 1965024 A1 EP1965024 A1 EP 1965024A1 EP 08102089 A EP08102089 A EP 08102089A EP 08102089 A EP08102089 A EP 08102089A EP 1965024 A1 EP1965024 A1 EP 1965024A1
Authority
EP
European Patent Office
Prior art keywords
wheel
bladed
bladed wheel
fixed
wheels
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08102089A
Other languages
English (en)
French (fr)
Other versions
EP1965024B1 (de
Inventor
Jérôme Dupeux
Jean-Pierre Lombard
Virenda Sharma
Samy Mitha
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 EP1965024A1 publication Critical patent/EP1965024A1/de
Application granted granted Critical
Publication of EP1965024B1 publication Critical patent/EP1965024B1/de
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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • 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
    • 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
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49327—Axial blower or fan

Definitions

  • the present invention relates to the field of turbomachines and aims a method for reducing the vibrations on the blades of a bladed wheel subject to periodic excitation resulting from disturbances in the gas flow through the turbomachine, produced by a bladed wheel or an obstacle near said wheel, one being generally mobile and the other fixed.
  • a turbomachine comprises one or more rotors formed of bladed wheels, that is to say of blades mounted on a mobile disc rotated about an axis, and one or more grids formed of fixed bladed wheels, that is to say not movable in rotation with respect to the axis above.
  • the vanes of the fixed and moving wheels are traversed by a gaseous fluid in a general direction parallel to the axis.
  • One of the main sources of excitation of the fixed or mobile vanes is wakes and pressure fluctuations generated by the obstacles adjacent to the vane.
  • These various obstacles, namely the blades of the upstream and downstream stages or the casing arms induce disturbances in the flow of fluid through the blades.
  • the scrolling of the vanes in these disturbances creates a synchronous harmonic excitation of the rotational speed of the rotor and generates an unsteady pressure field on the surface of the blade.
  • the blades are particularly sensitive parts because they must meet in terms of dimensioning requirements of aerodynamic performance, aeroacoustics and mechanical resistance to rotation, temperature and aerodynamic load. All of these aspects mean that these structures are sufficiently charged statically and that, given the requirements of service life, the amplitudes of vibrations that they undergo must remain low.
  • the aeroelastic coupling ie the coupling between the dynamics of the bladed wheels and the fluid flow, conditions the vibratory stability of the structure.
  • the sizing process is iterative. Vibration sizing is done to avoid the presence critical resonances in the operating range of the machine.
  • the assembly is validated at the end of the design cycle by a motor test on which the vibration amplitudes are measured. It sometimes appears high vibratory levels related to either resonances or vibratory instabilities. The development of the rotor concerned must then be redone which is particularly long and expensive.
  • the object of the present invention is to control, already during the design or development phase of the machine, the levels of vibratory response of the bladed wheels in a turbomachine structure comprising at least one mobile bladed wheel and one fixed bladed wheel traversed by a gas flow.
  • the invention thus aims at the treatment of the vibrations produced by the disturbances generated for example by one of the wheels in the gas flow on the other bladed wheel. It is aimed in a particular case disturbances generated on the gas flow by the wake of a fixed bladed wheel or an obstacle such as crank arms; these disturbances produce vibrations on the mobile downstream wheel.
  • the objective of the present invention is not limited to the control of vibration levels in a configuration where the bladed wheels are adjacent, it aims to control the vibratory responses on a bladed wheel for disturbances originating from upstream or downstream of the bladed wheel without being limited to adjacent wheels.
  • the invention also relates to aerodynamic vein-type excitation excitations generated by one or more samplings in the gas vein or by a distortion of the engine inlet sleeve, when the engine is a turbojet engine, in the event of crosswind or flight in incidence. These distortions are included in the term obstacle, afterwards.
  • Another object of the invention is the realization of a method that makes it possible to take the corrective measures that are required as early or as far upstream as possible in the process of designing and developing turbomachine bladed wheels.
  • the initial configuration on the fixed wheel is modified, whether this is the exciter wheel or the wheel undergoing excitation.
  • T y ⁇ * f ( ⁇ ) represents the generalized aerodynamic force for the eigenmode ⁇ .
  • the treatment of vibration phenomena comprises within the scope of the invention the implementation of means for reducing the modulus
  • a procedure to achieve this is to change the stacking axis of the studied blades in the direction tangential to the axis of rotation.
  • the profile of the blade of a blade is geometrically defined from the profiles of each of the parallel sections made between the root of the blade and its top. The sections thus form a stack along a curve that is called the stacking axis.
  • the profiles are determined aeromechanically.
  • a turbomachine structure here a compressor, comprises at least one bladed wheel 3 movable about an axis of rotation adjacent to at least one fixed bladed wheel 2 or 4.
  • the structure comprises a plurality of movable wheels separated by wheels fixed.
  • the relative movement of one wheel relative to the other within an axial gas flow, represented by the arrow F is a source of disturbances.
  • a first movable wheel 11 is influenced by a second fixed bladed wheel 12 while in its wake. This wake is the source of disturbances on the first moving wheel 11.
  • a first movable bladed wheel 11 ' is considered in its position upstream with respect to a second fixed wheel 12' and which undergoes the excitatory forces generated by the second downstream wheel 12 '.
  • the profile of a blade and its blade in particular is generally determined by a plurality of cuts made in the radial direction between the foot and the top.
  • the figure 6 shows a fixed blade 30 of a stationary turbomachine stage with a foot 31 and its platform, a top 32 and its platform, and in between, a blade 33 swept by the gas flow.
  • the blade 33 in position in the turbomachine is radially oriented relative to the axis of the latter.
  • the blade is geometrically defined by the individual profile of a plurality of sections C 1 , C 2 , C 3 ,... C p (p being of the order of 20) by planes p1, p2, ... pp tangents to this radial direction.
  • the profile of the blade swept by the gas flow is defined in the same way by cuts made in the tangent planes.
  • the module of the forced response y ( ⁇ ) of the blades of a first bladed wheel is reduced by searching for an adequate distribution of the components of the pressures to minimize the modulus of the generalized aerodynamic force associated with each of the eigen modes ⁇ .
  • the generalized aerodynamic force associated with an eigenmode is a multiplying factor that appears in each of the terms of the sum ⁇ .
  • the first two steps are to define the specifications in terms of aerodynamic performance of the structure comprising the two bladed wheels, and then to calculate the initial configuration of the bladed wheels.
  • This configuration includes the profiles of sections c 1 ,... C p and their stacking. It is generally carried out by aerodynamic iterations as is known to those skilled in the art.
  • alpha is the smallest possible value given the manufacturing tolerances.
  • Step 4 The procedure according to the invention is applied with the maximum vibratory level above as target.
  • the modulus of the aeroelastic forced response is minimized for a given mode knowing that it can be extended to any mode.
  • the method consists in determining the geometric offset ⁇ , illustrated on the figure 8 applied on the tangential stacking axis so as to minimize the vibratory response due to the disturbance, such as the wake.
  • spline / poles or any discrete bases or chosen to project the stacking law are used for example.
  • the optimization method can be any.
  • gradient method so-called “simulated annealing” method
  • genetic method ...
  • the quantity to be minimized is the modulus
  • Step 5 Perform a calculation of aeroelastic forced response y '( ⁇ ) on the modified blade to verify that the target in terms of maximum vibration level is reached. If this is not the case, a new profile definition is defined.
  • Step 6 once the target has been reached, it is verified that the aerodynamic performances are preserved by modifying the stacking axis of the blade concerned.
  • Step 7 the new definition of vane is retained; it meets the aerodynamic criteria in terms of performance and the mechanical criteria in terms of vibration levels.
  • the figure 9 shows an example of aspect that takes the dawn 30 of the figure 6 after application of the method of the invention.
  • the cuts c1, c2 ... cp are not aerodynamically modified. They have each undergone a tangential shift around the axis of the turbomachine.
  • each point represents the value of the angle ⁇ for each of the cuts C 1 to C p over the entire height of the blade of the blade. It can be seen that this value remains relatively low, lower in this example than 1 degree with respect to the position corresponding to the initial configuration.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08102089A 2007-02-27 2008-02-27 Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks Active EP1965024B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0701408A FR2913074B1 (fr) 2007-02-27 2007-02-27 Methode de reduction des niveaux vibratoires d'une roue aubagee de turbomachine.

Publications (2)

Publication Number Publication Date
EP1965024A1 true EP1965024A1 (de) 2008-09-03
EP1965024B1 EP1965024B1 (de) 2010-04-07

Family

ID=38562956

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08102089A Active EP1965024B1 (de) 2007-02-27 2008-02-27 Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks

Country Status (7)

Country Link
US (1) US8286347B2 (de)
EP (1) EP1965024B1 (de)
JP (1) JP5685358B2 (de)
CA (1) CA2621839C (de)
DE (1) DE602008000918D1 (de)
FR (1) FR2913074B1 (de)
RU (1) RU2447293C2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2935350A1 (fr) * 2008-08-27 2010-03-05 Snecma Methode de reduction des niveaux vibratoires d'une helice de turbomoteur.
GB2462921B (en) * 2008-08-27 2012-09-05 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed discs of a turbine engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140072433A1 (en) * 2012-09-10 2014-03-13 General Electric Company Method of clocking a turbine by reshaping the turbine's downstream airfoils
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
US11333171B2 (en) 2018-11-27 2022-05-17 Honeywell International Inc. High performance wedge diffusers for compression systems
US10871170B2 (en) 2018-11-27 2020-12-22 Honeywell International Inc. High performance wedge diffusers for compression systems

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995029331A2 (en) * 1994-04-19 1995-11-02 United Technologies Corporation Stator vane arrangement for successive turbine stages
WO1998036966A1 (en) * 1997-02-21 1998-08-27 California Institute Of Technology Rotors with mistuned blades
FR2824597A1 (fr) * 2001-05-11 2002-11-15 Snecma Moteurs Reduction de vibrations dans une structure comprenant un rotor et des sources de perturbation fixes
EP1528223A2 (de) * 2003-10-29 2005-05-04 ROLLS-ROYCE plc Entwurf vibrationsbelasteter Turbomaschinenschaufeln
EP1589191A1 (de) * 2004-04-20 2005-10-26 Snecma Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2076307C1 (ru) * 1994-06-30 1997-03-27 Анатолий Алексеевич Хориков Способ диагностики автоколебаний рабочего колеса осевой турбомашины
JPH11247605A (ja) * 1997-12-26 1999-09-14 United Technol Corp <Utc> タ―ボマシ―ンコンポ―ネントの振動緩衝方法及び装置
FR2811635B1 (fr) * 2000-07-13 2003-01-03 Eurocopter France Aeronef a voilure tournante a commande de pas electrique
US7191161B1 (en) * 2003-07-31 2007-03-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method for constructing composite response surfaces by combining neural networks with polynominal interpolation or estimation techniques
EP1658966A1 (de) * 2004-11-17 2006-05-24 General Electric Company Dämpfmaterial, Dämpfungseinrichtung, und Verfahren zum Entwurf einer Dämpfungseinrichtung

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995029331A2 (en) * 1994-04-19 1995-11-02 United Technologies Corporation Stator vane arrangement for successive turbine stages
WO1998036966A1 (en) * 1997-02-21 1998-08-27 California Institute Of Technology Rotors with mistuned blades
FR2824597A1 (fr) * 2001-05-11 2002-11-15 Snecma Moteurs Reduction de vibrations dans une structure comprenant un rotor et des sources de perturbation fixes
EP1528223A2 (de) * 2003-10-29 2005-05-04 ROLLS-ROYCE plc Entwurf vibrationsbelasteter Turbomaschinenschaufeln
EP1589191A1 (de) * 2004-04-20 2005-10-26 Snecma Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2935350A1 (fr) * 2008-08-27 2010-03-05 Snecma Methode de reduction des niveaux vibratoires d'une helice de turbomoteur.
GB2462921B (en) * 2008-08-27 2012-09-05 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed discs of a turbine engine
US8398372B2 (en) 2008-08-27 2013-03-19 Snecma Method for reducing the vibration levels of a propeller of a turbine engine

Also Published As

Publication number Publication date
JP5685358B2 (ja) 2015-03-18
RU2447293C2 (ru) 2012-04-10
CA2621839A1 (fr) 2008-08-27
US8286347B2 (en) 2012-10-16
CA2621839C (fr) 2014-10-21
JP2008208835A (ja) 2008-09-11
EP1965024B1 (de) 2010-04-07
RU2008107300A (ru) 2009-09-10
FR2913074A1 (fr) 2008-08-29
DE602008000918D1 (de) 2010-05-20
FR2913074B1 (fr) 2009-05-22
US20080206058A1 (en) 2008-08-28

Similar Documents

Publication Publication Date Title
EP1965024B1 (de) Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks
CA2647051C (fr) Procede de conception d&#39;une turbine multi-etages de turbomachine
FR2935350A1 (fr) Methode de reduction des niveaux vibratoires d&#39;une helice de turbomoteur.
EP1589191A1 (de) Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor
FR2931190A1 (fr) Ailette de turbine
CA2919155A1 (fr) Procede de modelisation d&#39;une pale d&#39;une helice non-carenee
FR2986864A1 (fr) Methode de mesure de la deformation d&#39;une aube de turbomachine au cours du fonctionnement de la turbomachine
EP3382146A1 (de) Kühlvorrichtung einer turbinenscheibe und zugehörige turbomaschine
FR2935427A1 (fr) Methode de reduction des niveaux vibratoires d&#39;un doublet et roues aubagees contrarotatives de turbomachine.
EP2809887A1 (de) Optimierung der lagerungspunkte der stützen von schaufeln in einem verfahren zur industriellen herstellung dieser schaufeln
EP3368748B1 (de) Verfahren zum absichtlichen verstimmen einer beschaufelten scheibe einer turbomaschine
Cravero et al. Numerical simulation of the performance of a twin scroll radial turbine at different operating conditions
EP2638249B1 (de) Optimierungsverfahren des profils einer rotorschaufel von einer turbomaschine
Bladh et al. Leakage-induced compressor blade excitation due to inter-segment gaps
Wang et al. Surge-elimination Strategy for Aero-engine Transient Control
US20230235674A1 (en) Cantilevered airfoils and methods of forming the same
Miura et al. Forced Response Excitation of a Compressor Stator Owing to Shock Wave Induced by Adjacent Rotor Blade
WO2022034083A1 (fr) Méthode et système de régulation de poussée d&#39;une turbomachine d&#39;aéronef
CN117386459A (zh) 用于叶片尖端间隙控制的可变流动路径壳体
FR3130321A1 (fr) Turbomachine non carénée comprenant des aubes de stator présentant des cordes différentes
BE1028302A1 (fr) Ouverture transitoire d’aubes statoriques dans un compresseur de turbomachine lors d’une acceleration
FR3130320A1 (fr) Turbomachine non carénée comprenant des aubes de stator présentant des cordes différentes
Cosi et al. Design, manufacturing and testing of a new family of steam turbine low pressure stages
FR3096159A1 (fr) Procédé de paramétrage d’un filtre numérique pour l’atténuation d’une fréquence associée à un mode de torsion d’une ligne de transmission de puissance d’un turbomoteur
Kenny et al. Multi-Disciplinary Design Tool for Axial Flow Turbines

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: 20080227

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 HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKX Designation fees paid

Designated state(s): DE FR GB

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

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

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: 602008000918

Country of ref document: DE

Date of ref document: 20100520

Kind code of ref document: P

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: 20110110

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

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: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SNECMA, FR

Effective date: 20170713

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

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: 20230119

Year of fee payment: 16

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

Ref country code: DE

Payment date: 20240123

Year of fee payment: 17

Ref country code: GB

Payment date: 20240123

Year of fee payment: 17