EP3472472B1 - Système de couches, turbine et procédé de production - Google Patents

Système de couches, turbine et procédé de production Download PDF

Info

Publication number
EP3472472B1
EP3472472B1 EP17739949.0A EP17739949A EP3472472B1 EP 3472472 B1 EP3472472 B1 EP 3472472B1 EP 17739949 A EP17739949 A EP 17739949A EP 3472472 B1 EP3472472 B1 EP 3472472B1
Authority
EP
European Patent Office
Prior art keywords
impeller
layer
base element
layer system
lcmn
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
EP17739949.0A
Other languages
German (de)
English (en)
Other versions
EP3472472A1 (fr
Inventor
Peter MARTINIUS
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.)
Siemens Energy BV
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP3472472A1 publication Critical patent/EP3472472A1/fr
Application granted granted Critical
Publication of EP3472472B1 publication Critical patent/EP3472472B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2263—Carbides of tungsten, e.g. WC

Definitions

  • the invention relates to an impeller of a turbo-machine, in particular a turbo-compressor, in particular a centrifugal turbo-compressor, wherein said impeller comprises a base element of a base material comprising blades being arranged along a circumferential direction of a rotational axis, wherein said blades comprise a leading edge and a trailing edge.
  • Said impeller comprising a layer system applied on said base element, wherein said layer system extends in a border area of said base element up to an outer surface, wherein said layer system comprises at least one layer of cladding material provided onto the base material.
  • the invention relates to a method to produce an impeller respectively according to the before mentioned type.
  • EP 2 135 698 A1 , EP 2 789 713 A1 , DE 10 2009 043097 relate to free standing blades being partly coated. These blades are generally used in steam turbines to withstand e.g. droplet erosion.
  • US 2011/229338 A1 discloses an impeller according to the preamble of claim 1.
  • the specific focus of the invention is the avoidance of erosion in turbo-compressors.
  • the rotating parts, especially the impellers of the turbo machine may suffer from a dramatic decrease in lifetime due to severe erosion wear.
  • Dust particles carries by a process fluid through the machine for example so called 'black dust', may have hardnesses between 230 up to 600HV 0.01 (Vickers hardness test).
  • the rotating parts of pipeline compressors are quickly damaged in particular at the leading edge and the trailing edge of impeller blades.
  • the invention proposes a layer system, an impeller and a method to produce such a layer system or an impeller as according to the respective independent claims.
  • the respective dependent claims refer to beneficial embodiments of the invention.
  • the layer system according to the invention comprises said base material and one or several of cladding material layers provided onto the base material. Further said layer system comprises a compressive residual stress layer extending from said outer surface into at least the outermost layer of cladding material. In case of several cladding material layers provided on a base material as part of the layer system said compressive residual stress layer may extend through several layers of cladding material from said outer surface and even extend into the base material as well. Preferably said compressive residual stress layer extends only in the outermost layer of cladding material.
  • a preferred embodiment of the invention is provided by generating said layer or layers of cladding material by gas tungsten arc welding (GTAW).
  • GTAW gas tungsten arc welding
  • a base material is X3CrNiMo13-4 (martensitic alloy).
  • X3CrNiMo13-4 material number: 1.4313 according to EN10250
  • weight percent wt%
  • Element Minimum Maximum Carbon (C) 0 0.05 Silicon (Si) 0 0.7 Mangan (Mn) 0,5 1.5 Chromium (Cr) 12.0 14.0 Molybdenum (Mo) 0.3 0.7 Nickel (Ni) 3,5 4.5 Sulfur (S) 0 0.015 Phosphor (P) 0 0.04 Nitrogen (N) 0 0.02 Iron base
  • Stellite 21 is Element Minimum Maximum Carbon (C) 0.15 0.40 Mangan (Mn) 0 1.0 Chromium (Cr) 25 30 Silicon (Si) 0 1.5 Molybdenum (Mo) 4.5 7.0 Nickel (Ni) 1.5 3 Iron (Fe) 0 5.0 Tungsten (W) 0 0.5 Cobald (Co) base others 0 1.0
  • One preferred embodiment provides that at least two layers of cladding material are provided to the base material and most preferably three layers of cladding material are provided. Preferably all three layers are of the same chemical composition and most preferably all three layers are of Stellite 21.
  • Another preferred embodiment of the layer system is provided by giving a heat treatment of up to three hours at 570°C to the base element for at least one time to eliminate residual welding stresses. Surprisingly it was found that the subsequent heat treatment as proposed does not impair the desirable high hardness of the cladding.
  • the most preferred application of the invention is the production of an impeller of a turbo-machine, in particular a turbo-compressor, in particular a centrifugal turbo-compressor, wherein said impeller comprises a base element of a base material comprising blades being arranged along a circumferential direction of a rotational axis, wherein said blades comprise a leading edge and a trailing edge, wherein said leading edge and said trailing edge belong to a surface treatment zone, wherein at least part of said surface treatment zone is a layer system as described and defined in several embodiments above.
  • these impeller blades are attached to a hub section of said base element and are extending radially and/or axially from said hub section.
  • Said impeller can be designed as a so called open type or closed type.
  • flow channels are circumferentially delimited by said blades, a hub section and a shroud section being attached to the blades tips respectively defining the flow channels in axial-radial direction.
  • the hub section defines the flow channels in axial-radial direction (see also figure 1, 2 regarding the difference).
  • the layer system in particular the layer system of the impeller is produced applying the following steps:
  • a further substep is conducted by: c) heat treatment of said base element.
  • the heat treatment of said base element after the shot peening improves the residual stress in the base element down to an acceptable minimum of the one hand and on the other hand it does not impair the desired high hardness of the Stellite cladding. Since the heat treatment and the shot peening change the geometry of the base element a final machining of the base element is preferably performed as a substep d).
  • a further forth step can be conducted as: 4) mounting a shroud section to said base element.
  • the shroud section is preferably welded to said base element, in particular to the blade tips of said base element.
  • a heat treatment may be performed afterwards. Due to the changes in geometry expected from welding and heat treatment a final machining may preferably be done afterwards.
  • the base element being an impeller of a turbo-machine preferably balancing of the impeller and overspeeding may be performed to improve operational behavior and minimize risk of any damage.
  • a preferred embodiment of the impeller is provided by machining the base element with additional grooves respectively recesses compared to the ordinary impeller in the area of the surface treatment zone where the layer system according to the invention is provided.
  • Theses recesses may be provided cumulatively or alternatively like the following:
  • FIG. 1 and figure 2 respectively show a 2-dimensional longitudinal section through an impeller according to the invention along a rotational axis X.
  • the impeller IMP rotates during operation in a turbo-machine, in particular in a turbo-compressor TC around the rotational axis X.
  • Said impeller IMP comprises a based element BE of a base material BM comprising blades BLA being arranged along a circumferential direction CDR of said rotational axis X.
  • These blades BLA comprise a leading edge LE and a trailing edge TE.
  • the terms 'leading edge LE' and 'trailing edge TE' refer to a process fluid flow direction during operation for which the impeller IPM is fluid dynamically designed.
  • Said leading edge LE and said trailing edge TE belong to a surface treatment zone STZ.
  • a layer system LSY is provided to said surface treatment zone STZ.
  • This layer system LSY is shown in figure 4 schematically in a longitudinal section in detail in a border area (shown as a detail in Figure 4 ) of said base element BE.
  • Said layer system LSY comprises said base material BM of said base element BE and extends in said border area of said base element BE up to an outer surface OSF.
  • said layer system LSY comprises three layers of cladding material, a first layer LCM1, a second layer LCM2 and a third layer LCM3. This number of layers is an example which what was found to be advantageous.
  • Figure 3 shows schematically the steps of the method according to the invention to produce a layer system LSY as part of a base element BE here an impeller IMP.
  • this example of figure 3 refers to the impeller IMP but basically includes the generation of a layer system according to the invention to other parts as well preferably rotating parts of turbo-machines.
  • step 0 a raw part is provided, which is subsequently machined into the basic shape of an impeller IMP during steps 1), 2).
  • step 2) a surface treatment zone STZ is defined.
  • the impeller IMP is machined with additional grooves in the area of the leading edge LE and the trailing edge TE belonging to the surface treatment zone STZ of the base element BE. These additional grooves respectively recesses RE are provided to avoid any protrusion due to the provision of the layer system LSY in this areas.
  • the final impeller IMP is meant to have the same fluid dynamic properties as any conventional impeller IMP.
  • step 3) a) the surface treatment zone STZ defined during step 2) is transformed at least partly into said layer system LSY by the substeps of: 3)a) cladding at least one layer of cladding material LCM1-LCMn to said base material BM of said surface treatment zone STZ.
  • step 3)a)a) a heat treatment is performed at 570°C for 2 hours to reduce stresses caused by the welding procedure of the cladding. Any deformations are eliminated during machining in step 3) a) b).
  • step 3) b) shot peening in the area of said layer system LSY is performed to improve surface hardness.
  • step 4 In case of producing a closed impeller configuration including a shroud section SRS said shroud section SRS is mounted to the blade's tips of the base element BE preferably by welding. Subsequently a heat treatment and final machining is performed during step 4) a). After not illustrated optional steps of balancing and overspeeding the impeller IMP is mounted during assembly in a turbo-compressor TC in step 5). Between all these steps of the method several examinations may be performed to detect any material defects like cracks, in particular magnetic particle examinations can be done as non-destructive examination procedures.
  • the resulting impeller IMP including the layer system LSY applied by gas tungsten arc welding cladding of Stellite 21 powder onto the base element BE or base material X3CrNiMo13-4 results in an erosion resistant rotating part having partly a high hardness of approximately 690HV0.01 after heat treatment. In these critical areas of the surface treatment zones STZ the impeller surface is therefore harder than the maximum particle hardness of approximately 600hv0.01.

Landscapes

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

Claims (12)

  1. Impulseur (IMP) d'un turbocompresseur (TC) centrifuge, l'impulseur (IMP) comprenant un élément (BE) de base en un matériau (BM) de base comprenant des aubes (BLA) disposées suivant une direction (CDR) circonférentielle d'un axe (X) de rotation,
    les aubes (BLA) comprenant un bord (LE) d'attaque et un bord (TE) de fuite, dans lequel
    le bord (LE) d'attaque et le bord (TE) de fuite appartiennent à une zone (STZ) de traitement de surface, dans lequel au moins une partie de la zone (STZ) de traitement de surface est un système (LSY) à couche, comprenant un matériau (BM) de base d'un élément (BE) de base, le système (LSY) à couche s'étendant dans une zone de bord de l'élément de base jusqu'à une surface (OSF) extérieure,
    dans lequel le système (LSY) à couche comprend au moins une couche de matériau (LCM1-LCMn) de placage prévue sur le matériau (BM) de base,
    caractérisé en ce qu'
    au moins la couche la plus à l'extérieur du matériau (LCMn) de plaquage appartient, au moins en partie, à une couche (CRSL) de contrainte résiduelle de compression,
    dans lequel la couche (CRSL) de contrainte résiduelle de compression s'étend de la surface (OSF) extérieure au moins dans la couche la plus à l'extérieur du matériau (LCMn) de placage.
  2. Impulseur (IMP) suivant la revendication 1,
    dans lequel la couche ou les couches de matériau (LCM1-LCMn) de placage est (sont) obtenue (s) par un soudage (GTAW) à l'arc sous gaz protecteur avec électrode de tungstène.
  3. Impulseur (IMP) suivant la revendication 1 ou 2,
    dans lequel le matériau (BM) de base est X3CrNiMo13-4 (1.4313).
  4. Impulseur (IMP) suivant les revendications 1, 2 u 3,
    dans lequel le matériau d'au moins une couche du matériau (LCM1-LCMn) de placage est la stellite 21.
  5. Impulseur (IMP) suivant la revendication 1,
    dans lequel l'élément (BE) de base comprend une partie (HSC) de moyeu et des aubes (BLA) d'impulseur partant radialement et/ou axialement de la partie (HSC) de moyeu.
  6. Procédé de fabrication d'un impulseur (IMP) ayant un système (LSY) à couche suivant l'une des revendications 1 à 5,
    comprenant les stades suivants :
    1) usinage d'un élément (BE) de base en un matériau (BM) de base,
    2) définition des zones (STZ) de traitement de surface,
    3) transformation d'au moins une partie de la zone (STZ) de traitement de surface en un système (LSY) à couche par les sous-stades de :
    a) placage d'au moins une couche de matériau (LCM1-LCMn) de placage sur le matériau (BM) de base de la zone (STZ) de traitement de surface,
    b) grenaillage d'au moins la région de la zone (STZ) de traitement de surface dans la région du système (LSY) à couche.
  7. Procédé suivant la revendication 6,
    dans lequel on effectue un autre sous-stade :
    c) traitement thermique de l'élément (BE) de base.
  8. Procédé suivant la revendication 7,
    dans lequel on effectue un autre sous-stade :
    d) usinage final de l'élément (BE) de base.
  9. Procédé suivant au moins l'une des revendications 6 à 8 précédentes,
    dans lequel on effectue un autre stade :
    4) montage d'une partie (SRS) de virole sur l'élément (BE) de base.
  10. Procédé suivant les revendications 6, 7, 8 ou 9,
    dans lequel le matériau (LCM1-LCMn) de placage en couche est/sont obtenu (s) par un soudage ((GTAW) à l'arc sous gaz protecteur à électrode de tungstène.
  11. Procédé suivant les revendications 6, 7, 8, 9 ou 10,
    dans lequel le matériau (BM) de base est X3CrNiMo13-4 (1.4313).
  12. Procédé suivant les revendications 6, 7, 8, 9, 10 ou 11, dans lequel la couche du matériau (LCM1-LCMn) de placage est en stellite 21.
EP17739949.0A 2016-08-10 2017-07-10 Système de couches, turbine et procédé de production Active EP3472472B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP16183478.3A EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production
PCT/EP2017/067260 WO2018028908A1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine, procédé de production

Publications (2)

Publication Number Publication Date
EP3472472A1 EP3472472A1 (fr) 2019-04-24
EP3472472B1 true EP3472472B1 (fr) 2020-04-22

Family

ID=56618048

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16183478.3A Withdrawn EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production
EP17739949.0A Active EP3472472B1 (fr) 2016-08-10 2017-07-10 Système de couches, turbine et procédé de production

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP16183478.3A Withdrawn EP3282130A1 (fr) 2016-08-10 2016-08-10 Système de couches, turbine et procédé de production

Country Status (4)

Country Link
EP (2) EP3282130A1 (fr)
CN (1) CN109642583A (fr)
RU (1) RU2708187C1 (fr)
WO (1) WO2018028908A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3708774A1 (fr) * 2019-03-13 2020-09-16 Siemens Aktiengesellschaft Aube directrice et cascade fixe pour une turbomachine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2483528C (fr) * 2002-10-09 2015-07-21 Ishikawajima-Harima Heavy Industries Co., Ltd. Element rotatif et procede d'enduction dudit element
FR2861143B1 (fr) * 2003-10-20 2006-01-20 Snecma Moteurs Aube de turbomachine, notamment aube de soufflante et son procede de fabrication
GB0425088D0 (en) * 2004-11-13 2004-12-15 Holset Engineering Co Compressor wheel
US7304266B2 (en) * 2004-12-09 2007-12-04 General Electric Company Laser shock peening coating with entrapped confinement medium
CN100540208C (zh) * 2006-12-22 2009-09-16 沈阳大陆激光技术有限公司 一种离心压缩机流道叶片的修复工艺
US8471168B2 (en) * 2008-06-19 2013-06-25 General Electric Company Methods of treating metal articles and articles made therefrom
DE102009043097A1 (de) * 2009-09-25 2011-03-31 Siemens Aktiengesellschaft Laufschaufel zur Verwendung in Zweiphasenströmungen sowie Verfahren zum Herstellen einer solchen Laufschaufel
GB2475533B (en) * 2009-11-21 2016-04-13 Cummins Turbo Tech Ltd Compressor wheel
IT1397057B1 (it) * 2009-11-23 2012-12-28 Nuovo Pignone Spa Girante centrifuga e turbomacchina
US9534499B2 (en) * 2012-04-13 2017-01-03 Caterpillar Inc. Method of extending the service life of used turbocharger compressor wheels
US9103035B2 (en) * 2013-04-10 2015-08-11 General Electric Company Erosion resistant coating systems and processes therefor
CN104279186A (zh) * 2014-09-17 2015-01-14 杭州杭氧透平机械有限公司 一种大流量超大直径半铣半焊闭式三元叶轮及制造方法
CN105200226A (zh) * 2015-08-21 2015-12-30 江苏大学 一种提高金属材料疲劳寿命的方法

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
EP3282130A1 (fr) 2018-02-14
WO2018028908A1 (fr) 2018-02-15
EP3472472A1 (fr) 2019-04-24
RU2708187C1 (ru) 2019-12-04
CN109642583A (zh) 2019-04-16

Similar Documents

Publication Publication Date Title
JP5236263B2 (ja) 回転アセンブリ部品及び部品の製造方法
US8021120B2 (en) Turbine blade with a cover plate and a protective layer applied to the cover plate
US5823745A (en) Method of repairing a steam turbine rotor
EP2388091B1 (fr) Turbine à enveloppe avec materiaux à gradient de propriétés et procédé
US20130104397A1 (en) Methods for repairing turbine blade tips
US20160010488A1 (en) Wear protection arrangement for a turbomachine, process and compressor
US10513782B2 (en) Dual alloy blade
EP1564371A2 (fr) Procédé pour la réparation de pièce coulée
EP3472472B1 (fr) Système de couches, turbine et procédé de production
EP2999310B1 (fr) Système et procédé de réparation d'aubes
EP2716873A2 (fr) Carénage de turbine bimétallique et procédé de fabrication
US20140030109A1 (en) low-Modulus Gas-Turbine Compressor Blade
EP3095959A1 (fr) Procédé de conception et de fabrication de pale de rotor
EP2230037A1 (fr) Procédé de fabrication d'une hélice à microstructure double
US9931719B2 (en) Method for repairing a receiving hook for guide vanes
US10280801B2 (en) Turbine component and turbine shroud assembly
US8177516B2 (en) Shaped rotor wheel capable of carrying multiple blade stages
US20040261265A1 (en) Method for improving the wear resistance of a support region between a turbine outer case and a supported turbine vane
US11066933B2 (en) Rotor shaft and method for producing a rotor shaft
US20170198584A1 (en) Systems and methods for repairing a component of a rotary machine
EP4001657B1 (fr) Carénage de roue renforcé par pulvérisation à froid
US11725260B1 (en) Compositions, articles and methods for forming the same
CN115011845A (zh) 抗微动磨损涂层组合物以及涂层部件
JP2022088828A (ja) 地熱タービンの高耐食静翼、地熱タービンの静翼翼列および地熱タービンの高耐食静翼の製造方法

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190109

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

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
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: 20191209

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: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017015306

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1260477

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200515

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200422

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS ENERGY B.V.

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: 20200822

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: 20200422

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: 20200422

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: 20200722

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: 20200824

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: 20200723

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: 20200422

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: 20200422

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1260477

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200422

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

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: 20200722

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: 20200422

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: 20200422

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: 20200422

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: 20200422

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017015306

Country of ref document: DE

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: 20200422

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: 20200422

Ref country code: AT

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: 20200422

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: 20200422

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: 20200422

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: 20200422

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: 20200422

Ref country code: ES

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: 20200422

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602017015306

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: 20200422

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: 20200422

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: 20200422

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20210125

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200731

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

Ref country code: FR

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

Effective date: 20200731

Ref country code: CH

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

Effective date: 20200731

Ref country code: LU

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

Effective date: 20200710

Ref country code: LI

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

Effective date: 20200731

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: 20210202

Ref country code: BE

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

Effective date: 20200731

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: 20200422

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: 20200710

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

Effective date: 20210710

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: 20210710

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: 20200422

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: 20200422

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: 20200422

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: 20200422