EP3289182A1 - Aube de turbine - Google Patents

Aube de turbine

Info

Publication number
EP3289182A1
EP3289182A1 EP16733363.2A EP16733363A EP3289182A1 EP 3289182 A1 EP3289182 A1 EP 3289182A1 EP 16733363 A EP16733363 A EP 16733363A EP 3289182 A1 EP3289182 A1 EP 3289182A1
Authority
EP
European Patent Office
Prior art keywords
blade
wall thickness
transition
airfoil
turbine blade
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
EP16733363.2A
Other languages
German (de)
English (en)
Other versions
EP3289182B1 (fr
Inventor
Björn Buchholz
Ralph Gossilin
Daniela Koch
Marco Schüler
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 Global GmbH and Co KG
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP3289182A1 publication Critical patent/EP3289182A1/fr
Application granted granted Critical
Publication of EP3289182B1 publication Critical patent/EP3289182B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • 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

Definitions

  • Turbine blade the invention relates to a turbine blade according to the Gat ⁇ tung term of claim 1.
  • Hollow turbine blades in particular gas turbine blades, have in the region of a transition from the blade to
  • a turbine blade with an extended life is also known from EP 1 355 041 AI, wherein the contour of the transition from the blade to the platform in the blade interior is adapted to obtain in the transition region a blade wall thickness, which is approximately the wall thickness of the rest ⁇ corresponding blade.
  • the contour is ent ⁇ long the entire, closed circulation, ie along the platform adapted.
  • the reduced wall thickness for reasons of strength, can adversely affect the life of the turbine blade, which is undesirable.
  • the invention is characterized in that it comprises a defining a cavity inside surface in the region of the ⁇ gear, whose contour is adapted in a first section of the inner surface in such a way that in the region of the transition has a substantially uniform blade wall thickness available for a corresponding to the preamble turbine blade is, wherein in the transition of the contour of the inner surface at a second inner surface portion of the airfoil, which is opposite the leading edge, such that there the blade wall thickness is increased, compared with the show ⁇ felwanddicke the transition of the first portion of the inner ⁇ surface.
  • the contour profile is at an inner surface of the blade opposite the leading edge such that there the blade wall thickness is increased compared to the show ⁇ felwanddicke the transition, away from the local inner surface ⁇ section.
  • the second inner surface portion extends with increased blade wall thickness starting at the front edge of the airfoil along the suction sidewall and / or the pressure sidewall along the profile centerline to a position equal to or less than 9% of the length of the profile centerline.
  • the strength can, in particular in the pre ⁇ derkanten Scheme of the turbine blade, locally enlarged ⁇ the, resulting in an increased service life of the respective areas.
  • the platform has a platform wall thickness and the blade ⁇ blade off the transition a blade wall thickness, wherein in the region with substantially uniform blade wall thickness of the transition, the ratio of blade wall thickness to platform wall thickness between 0.5 and 1 lies.
  • Such a turbine blade can be cooled particularly homogeneously, which reduces thermomechanical stresses in the material of the turbine blade.
  • FIG. 1 shows a plan view of the foot region of a turbine blade designed as a guide face
  • FIG. 2 shows a longitudinal section through the turbine blade according to FIG. 1 along the section line II-II.
  • the 1 shows in perspective view a turbine blade 10.
  • the perspective is chosen so that the top ⁇ view of a mounting portion 12 of the vane as configured turbine blade 10 is shown.
  • FIG 2 the longitudinal section through the turbine blade 10 according to the section line II-II of FIG 1 is shown.
  • the turbine blade 10 has, along a radial axis 14, successively the fastening region 12, an adjacent blade plate 16 and an airfoil 18.
  • a blade root 20 is formed, which serves for fastening ⁇ tion of the turbine blade 10 to a turbine vane support, not shown.
  • the representation of the invention takes place by way of example with reference to egg ⁇ ner designed as a guide blade with two platforms turbine blade. Nevertheless, other embodiments are possible, in particular, the turbine blade can also be configured as a blade of a turbine. At least the main body of the turbine blade is produced by a casting method and comprises at least the blade 18, as ⁇ at least one platform 16. As is apparent from the figures, the invention ⁇ turbine blade 10 and in particular its blade 18 is designed to be hollow inside, so that it comprises a cavity 25, which may be configured in a known manner as a cooling channel with or without impingement cooling.
  • the airfoil 18 extends from a front edge 28 to a trailing edge 30.
  • the airfoil 18 comprises only schematically indicated in Figure 1 suction side show ⁇ felwand 32 and a pressure-side vane wall 34.
  • the vane walls 32, 34 a wall thickness D. which is essentially consistent.
  • a transition 36 the surface on the outer top of the turbine blade is rounded 10 and thus fillet- ⁇ like.
  • Inside 18 has the blade to a temperature the outer surfaces FLAE ⁇ opposite inner surface. This is such in the area of the suction-side blade wall 32 so as to partially ⁇ as the outer contour of the transition, ie, along the radial axis 14 of a blade tip to the blade root, is Designed to fit, so that there uniform the transition 36 in the Wesent ⁇ union Vane wall thickness Dl is present.
  • the inner surface in the region of the transition 36 comprises a second mecanicab ⁇ section 40 opposite the front edge 28, the contour of which is such that there the blade wall thickness (D 2 ) is increased compared to the blade wall thickness Di of the transition away from the second inner ⁇ surface portion 40th in other words, the second interior surface portion 40 is only located in the immediate Conversely ⁇ bung of the front edge and forms, with inner surface of the remainder of the airfoil along the radial direction 14 and in longitudinal section viewed a straight line, whereas the rest of the inner surface of the suction and / or Pressure side in the transition, ie, a first inner surface portion 41 under Beibe ⁇ attitude of an approximately uniform blade wall thickness Di is curved. Consequently, starting from the front edge 28 along the transition 36, the second inner surface section 40 with the increased wall thickness D2 is followed by the first inner surface section 41 having a wall thickness Di which corresponds to the wall thickness D of the airfoil.
  • the invention relates to a cast turbine blade or vane 10 having a platform 16 and a thereto ⁇ arranged hollow airfoil 18, wherein the airfoil 18 includes a pressure-side blade wall 34 and a suction-side show ⁇ felwand 32, a centrally reasonable longitudinally thereof extend arcuate tread center line 42 from a common leading edge 28 to a common trailing edge 30 and having an outer contour transition 36 between the blade and platform 36, wherein the blade walls 32, 34 each have a locally to be detected blade wall thickness D, wherein the turbine blade inside a contour profile which is partially adapted to the outer contour of the transition 36 in such a way that in the region of the transition 36, a substantially uniform blade wall thickness is present.
  • the contour at one of the leading edge 28 opposite second inner surface portion 40 of the airfoil is such that there the blade wall thickness is increased compared to the blade wall thickness of the transition away from the leading edge ,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube de turbine (10) coulée comportant une plateforme (16) sur laquelle est agencé un aubage (18) creux, l'aubage (18) comprenant une paroi d'aube (34) côté pression et une paroi d'aube (32) côté aspiration, qui s'étendent le long d'une ligne médiane de profil (42) courbe centrale d'un bord avant (28) commun jusqu'à un bord arrière (30) commun, et comportant une transition (36) présentant un contour extérieur entre l'aubage et la plateforme (16). Les parois d'aube (32, 34) présentent respectivement une épaisseur de paroi d'aube (D) à détecter localement, l'aube de turbine présente un contour intérieur, qui est adapté au moins en partie au contour extérieur de la transition (36) de telle manière qu'on obtient dans la zone de la transition (36) une épaisseur de paroi d'aube sensiblement uniforme. L'invention vise à prolonger la durée de vie d'une aube de turbine de ce type. À cet effet, le contour est configuré dans la transition au niveau d'une section de surface (40) de l'aubage opposée au bord avant (28) de telle manière qu'au niveau de cette section, l'épaisseur de paroi d'aube est plus grande que l'épaisseur de paroi d'aube de la transition en retrait du bord avant.
EP16733363.2A 2015-07-03 2016-06-21 Aube de turbine Active EP3289182B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15175301.9A EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine
PCT/EP2016/064274 WO2017005484A1 (fr) 2015-07-03 2016-06-21 Aube de turbine

Publications (2)

Publication Number Publication Date
EP3289182A1 true EP3289182A1 (fr) 2018-03-07
EP3289182B1 EP3289182B1 (fr) 2020-03-25

Family

ID=53514053

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15175301.9A Withdrawn EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine
EP16733363.2A Active EP3289182B1 (fr) 2015-07-03 2016-06-21 Aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP15175301.9A Withdrawn EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine

Country Status (5)

Country Link
US (1) US10301944B2 (fr)
EP (2) EP3112589A1 (fr)
JP (1) JP6469897B2 (fr)
CN (1) CN107735548B (fr)
WO (1) WO2017005484A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10422236B2 (en) * 2017-08-03 2019-09-24 General Electric Company Turbine nozzle with stress-relieving pocket
US10655485B2 (en) * 2017-08-03 2020-05-19 General Electric Company Stress-relieving pocket in turbine nozzle with airfoil rib
DE102018209610A1 (de) 2018-06-14 2019-12-19 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine
JP7419002B2 (ja) * 2019-09-12 2024-01-22 三菱重工業株式会社 ストラットカバー、排気車室およびガスタービン
US11578607B2 (en) * 2020-12-15 2023-02-14 Pratt & Whitney Canada Corp. Airfoil having a spline fillet

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1049872B (fr) 1953-06-04 1954-02-05
JP3411775B2 (ja) 1997-03-10 2003-06-03 三菱重工業株式会社 ガスタービン動翼
CA2334071C (fr) 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Aube mobile de turbine a gaz
JP2001271603A (ja) * 2000-03-24 2001-10-05 Mitsubishi Heavy Ind Ltd ガスタービン動翼
DE10217390A1 (de) * 2002-04-18 2003-10-30 Siemens Ag Turbinenschaufel
GB2395987B (en) 2002-12-02 2005-12-21 Alstom Turbine blade with cooling bores
US7371046B2 (en) * 2005-06-06 2008-05-13 General Electric Company Turbine airfoil with variable and compound fillet
CH698109B1 (de) 2005-07-01 2009-05-29 Alstom Technology Ltd Turbomaschinenschaufel.
CN101627182B (zh) 2005-07-27 2013-02-27 西门子公司 用于燃气轮机的冷却的涡轮叶片和这种涡轮叶片的用途
JP4738176B2 (ja) 2006-01-05 2011-08-03 三菱重工業株式会社 冷却翼
DE502006003548D1 (de) 2006-08-23 2009-06-04 Siemens Ag Beschichtete Turbinenschaufel
JP5490091B2 (ja) 2008-03-28 2014-05-14 アルストム テクノロジー リミテッド ガスタービン用案内翼
JP5479032B2 (ja) 2009-11-05 2014-04-23 三菱重工業株式会社 タービンホイール
EP2476863A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
EP2700787B1 (fr) 2011-04-22 2018-04-04 Mitsubishi Hitachi Power Systems, Ltd. Aube et machine rotative
CH705187A1 (de) * 2011-06-17 2012-12-31 Alstom Technology Ltd Gegossene Turbinenschaufel.

Also Published As

Publication number Publication date
JP2018524511A (ja) 2018-08-30
CN107735548B (zh) 2019-07-12
JP6469897B2 (ja) 2019-02-13
CN107735548A (zh) 2018-02-23
US10301944B2 (en) 2019-05-28
US20180187551A1 (en) 2018-07-05
WO2017005484A1 (fr) 2017-01-12
EP3289182B1 (fr) 2020-03-25
EP3112589A1 (fr) 2017-01-04

Similar Documents

Publication Publication Date Title
DE602004006323T2 (de) Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine
EP2059655B1 (fr) Aube mobile refroidie pour turbines
EP3289182A1 (fr) Aube de turbine
EP3176370B1 (fr) Ensemble d'aubes directrices pour turbomachine
EP1895102B1 (fr) Aube de turbine revêtu
EP2245273B1 (fr) Aube de turbine destinée à une turbine à gaz fixe
WO2009129786A1 (fr) Chemin d'écoulement reproduit d'une turbomachine axiale destiné à réduire l'écoulement secondaire
EP1745195B1 (fr) Aube de turbomachine
EP1757773A1 (fr) Aube creuse de turbine
EP2161411A1 (fr) Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion
EP3056677B1 (fr) Aube et turbomachine
EP3460187B1 (fr) Aube pour une turbomachine
WO2015158514A1 (fr) Aube de turbine et turbine
WO2019086065A1 (fr) Conduit intermédiaire produit par fabrication additive et destiné à être agencé entre un compresseur basse pression et un compresseur haute pression, ainsi que procédé de fabrication dudit conduit
EP2650475B1 (fr) Pale pour une turbomachine, agencement d'aubes ainsi que la turbomachine
EP2396515B1 (fr) Aube mobile pour une turbomachine et turbomachine
EP4400694A1 (fr) Blisk
DE942236C (de) Einrichtung zur Schaufelbefestigung an axial durchstroemten Turbomaschinen, insbesondere Gasturbinen
DE102018212334B4 (de) Abgasturbolader mit Turbinenrad mit Winglets
WO2017108661A1 (fr) Aube de turbine pour une turbomachine thermique
WO2025228558A1 (fr) Aube de turbine à nervures internes améliorées, et noyau de moule
EP3199760A1 (fr) Aube de turbine dotée d'un élément d'étranglement
WO2014009074A1 (fr) Aube de turbine pour turbine à gaz
WO2015120995A1 (fr) Aube de turbine et procédé de fabrication ou de rectification d'une aube de turbine
CH700000A1 (de) Verfahren zum giesstechnischen Herstellen einer Schaufel sowie Schaufel für eine Gasturbine.

Legal Events

Date Code Title Description
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: 20171130

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: 20191107

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: AT

Ref legal event code: REF

Ref document number: 1248795

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200415

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: 502016009288

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

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: 20200625

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: 20200325

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: 20200325

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

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: 20200626

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: 20200325

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: 20200325

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: 20200625

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200325

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: 20200325

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

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: 20200325

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: 20200325

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: 20200325

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: 20200325

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: 20200325

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: 20200818

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: 20200725

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: 20200325

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502016009288

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502016009288

Country of ref document: DE

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

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG

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: 20200325

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: 20200325

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: 20200325

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: 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: 20200325

26N No opposition filed

Effective date: 20210112

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

Ref country code: LU

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

Effective date: 20200621

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

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: 20200621

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: 20200630

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: 20200325

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20211202 AND 20211209

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: 20200325

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: 20200325

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: 20200325

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: 20200325

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: 20200325

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1248795

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210621

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: 20210621

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20231222

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

Ref country code: DE

Payment date: 20250626

Year of fee payment: 10

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

Ref country code: GB

Payment date: 20250617

Year of fee payment: 10

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

Ref country code: FR

Payment date: 20250624

Year of fee payment: 10

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

Ref country code: SE

Payment date: 20250619

Year of fee payment: 10

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

Ref country code: IT

Payment date: 20250623

Year of fee payment: 10

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

Ref country code: CH

Payment date: 20250701

Year of fee payment: 10