EP2728114A1 - Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine und Schaufel für eine Turbomaschine - Google Patents

Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine und Schaufel für eine Turbomaschine Download PDF

Info

Publication number
EP2728114A1
EP2728114A1 EP12190755.4A EP12190755A EP2728114A1 EP 2728114 A1 EP2728114 A1 EP 2728114A1 EP 12190755 A EP12190755 A EP 12190755A EP 2728114 A1 EP2728114 A1 EP 2728114A1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
cooling device
turbomachine
platform cooling
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
EP12190755.4A
Other languages
English (en)
French (fr)
Other versions
EP2728114B1 (de
Inventor
Janos Szijarto
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 AG
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
Priority to EP12190755.4A priority Critical patent/EP2728114B1/de
Publication of EP2728114A1 publication Critical patent/EP2728114A1/de
Application granted granted Critical
Publication of EP2728114B1 publication Critical patent/EP2728114B1/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to a blade for a turbomachine and more particularly to a platform cooling device for the blade of the turbomachine.
  • the blade typically includes an airfoil portion and a root portion separated by a blade platform.
  • the airfoil portion of the blade is cooled by directing a cooling fluid to flow through radial passages formed in the airfoil portions of the blades.
  • a number of small axial passages are formed inside the blade airfoils that connect with one or more of the radial passages so that cooling air is directed over the surfaces of the airfoils, such as the leading and trailing edges or the suction and pressure surfaces. After the cooling air exits the blade it enters and mixes with the hot gas flowing through the turbine section.
  • cooling of blade platform is difficult since cooling air was not utilized in cooling the blade platform, the upper surfaces of which are exposed to the flow of hot gas from the combustors.
  • cooling of blade platform is achieved by providing film cooling by flowing a portion of the cooling air discharged from the upstream vanes over the upper surfaces of the blade root platforms, however, the film cooling is insufficient to adequately cool the blade root platform resulting in oxidation and cracking in the platforms.
  • US patent number 6,120,249 describes a cooling concept for a gas turbine blade platform wherein cooling air passages are formed in the blade root platform which includes cavities formed in a radially inward facing surface of an overhanging surface of the blade airfoil. An impingement plate directs cooling air into these cavities for providing cooling.
  • the object is achieved by providing a platform cooling device for a blade of a turbomachine according to claim 1 and a blade for a turbomachine according to claim 7.
  • a platform cooling device for a blade of a turbomachine includes a first portion to be positioned at a platform of the blade, a second portion arranged at an angle to the first portion, to be positioned at a root portion of the blade, an inlet for a cooling fluid on the second portion, and a channel for directing the cooling fluid from the inlet to a plurality of impingement holes for releasing the cooling fluid at the first portion.
  • the second portion comprises a plurality of dumping holes for the cooling fluid.
  • the dumping holes allow the cooling fluid to exit the platform cooling device into a space between the blades and from there as a leakage into the hot gas flow path.
  • the platform cooling devices includes a first protrusion at the first portion for attaching to the platform and a second protrusion at second portion for attaching to the root portion such that a cavity is formed between the device and the blade for directing the cooling fluid from the impingement holes to the dumping holes.
  • Protrusions at the first portion and the second portion allow an ease of attachment of the device with the platform and the root portion respectively. Due to the protrusions a cavity is formed between the device and the blade thereby allowing the impinged cooling fluid which gets heated after impinging on the blade platform, this heated cooling fluid is directed to the dumping holes through the cavity formed between the platform cooling device and the blade.
  • the platform cooling device is brazed at the first protrusion and the second protrusion to the blade. Brazing does not melt the base metal of the joint and allows tighter control over tolerances, hence producing a clean joint. Furthermore, brazing allows dissimilar metals to be joined. Additionally, brazing produces less thermal distortion due to uniform heating of the brazed piece.
  • the platform cooling device is formed from a nickel alloy.
  • Nickel alloys can be easily brazed, have high strength, can withstand high temperatures and are corrosion resistant.
  • the platform cooling device is formed through laser sintering.
  • Laser sintering technique provides an efficient way of forming a desired three dimensional shape with channels to ensure cooling effectiveness.
  • a blade for a turbo machine includes an airfoil portion and a root portion, wherein the root portion comprises a platform from which the airfoil portion extends in a radial direction, a platform cooling device disposed at the root portion, the device having a first portion and a second portion, wherein the first portion is adapted to be positioned at the platform and the second portion is adapted to be positioned at the root portion along the radial direction characterised in that the platform cooling device includes an inlet for a cooling fluid at the second portion, wherein the inlet is fluidly connected to a cooling fluid channel in the root portion, and a plurality of holes on the first portion for impinging the cooling fluid from the inlet against the platform, wherein the inlet is in flow communication with the holes for the cooling fluid.
  • the platform cooling device allows cooling fluid to be directed to portions of the platform where cooling is desired, obviating the need for making channels or
  • the first portion of the platform cooling device is attached to the platform at a first end and the second portion of the platform cooling device is attached to the root portion at a second end. Attaching the platform cooling device at the first end and the second end allows the device to be securely fixed and also create a cavity between the platform cooling device and the blade, which allows the flow of cooling fluid.
  • the cavity extends from the first end to the second end, which allows the impinged fluid to further cool the portion of the blade in the cavity while travelling from the first end to the second end.
  • Embodiments of the present invention described below relate to a blade component in a turbo machine. However, the details of the embodiments described in the following can be transferred to a vane component without modifications, that is the terms "blade” or "vane” can be used in conjunction, since they both have the shape of an airfoil.
  • the turbomachine may include a gas turbine, a steam turbine, a turbofan and the like.
  • FIG. 1 is a schematic diagram of an exemplary blade 1 of a rotor (not shown) of a turbomachine, such as a gas turbine.
  • the blade 1 includes an airfoil portion 2 and a root portion 3.
  • the airfoil portion 2 projects from the root portion 3 in a radial direction as depicted, wherein the radial direction means a direction perpendicular to the rotation axis of the rotor.
  • the airfoil portion 2 extends radially along a longitudinal direction of the blade 1.
  • the blade 1 is attached to a body of the rotor (not shown), in such a way that the root portion 3 is attached to the body of the rotor whereas the airfoil portion 2 is located at a radially outermost position.
  • the airfoil portion 2 has an outer wall including a pressure side 6, also called pressure surface, and a suction side 7, also called suction surface.
  • the pressure side 6 and the suction side 7 are joined together along an upstream leading edge 4 and a downstream trailing edge 5, wherein the leading edge 4 and the trailing edge 5 are spaced axially from each other as depicted in FIG. 1 .
  • a platform 9 is formed at an upper portion of the root portion 3.
  • the airfoil portion 2 is connected to the platform 9 and extends in the radial direction outward from the platform 9.
  • cooling holes 8 are present on the pressure side 6 and the suction side 7 of the blade as depicted in FIG. 1 . These cooling holes 8 aid in film cooling of the blade 1.
  • the blade 1 includes a platform cooling device 10 disposed at the root portion 3 of the blade 1 for cooling the platform 9.
  • the exemplary platform cooling device 10 will be described in more detail hereinafter.
  • the platform cooling device 10 includes a first portion 11 and a second portion 12 wherein the second portion 12 is at an angle to the first portion 11.
  • angle between the first portion 11 and the second portion 12 may be from about 80 degrees to about 110 degrees.
  • first portion 11 and the second portion 12 are perpendicular to each other.
  • the platform cooling device 10 includes a first protrusion 14 at the first portion 11 and a second protrusion 16 at the second portion 12.
  • the first portion 11 of the platform cooling device 10 is adapted to be positioned at the platform 9 of the blade 1 and the second portion 12 is adapted to be positioned at the root portion 3 of the blade 1.
  • first protrusion 14 aids in attaching the first portion 11 of the platform cooling device 10 with the platform 9
  • second protrusion 16 aids in attaching the second portion 12 of the platform cooling device 10 with the root portion 3 of the blade 1.
  • An inlet 18 for a cooling fluid such as, but not limited to cooling air, is provided at the second portion 12 of the platform cooling device 10, as depicted in FIG. 2 .
  • the inlet 18 is fluidly connected to a cooling fluid channel (not shown in FIG. 2 ) in the root portion 3 of the blade 1.
  • a plurality of impingement holes 20 is present in the first portion 11 of the platform cooling device 10.
  • a channel (not shown in FIG. 2 ) within the platform cooling device 10 directs the cooling fluid from the inlet 18 to the plurality of impingement holes 20 for releasing the cooling fluid at the first portion 11. The released fluid impinges on a surface of the platform 9 thereby cooling the platform 9.
  • the platform cooling device includes a plurality of dumping holes 22 for letting out the impinged fluid from the platform cooling device 10.
  • the dumping holes 22 are located on the second portion 12 of the platform cooling device 10.
  • the platform cooling device 10 is manufactured by using laser sintering technique.
  • the platform cooling device 10 may be formed of a material which is corrosion resistant and is capable of withstanding high temperatures. More particularly, the platform cooling device 10 may be formed of a nickel based alloy.
  • FIG. 3 shows a sectional view 25 of the blade 1 depicting the root portion 3 and the platform 9 with the platform cooling device 10.
  • the platform cooling device 10 includes the first portion 11 and the second portion 12 substantially perpendicular to each other.
  • the first portion 11 is attached to the platform 9 at a first end 32 and the second portion 12 is attached to the root portion 3 at a second end 34.
  • the platform cooling device 10 is brazed with the platform 9 and the root portion 3 at the first end 32 and the second end 34 respectively.
  • the platform cooling device 10 may be attached by welding at the first end 32 and the second end 34. More particularly, brazing or welding is done at the first protrusion 14 and the second protrusion 16 thereby attaching the platform cooling device 10 at the first end 32 and the second end 34 respectively.
  • a cavity 30 is formed between the blade 1 and the platform cooling device 10 after attaching the platform cooling device 10 to the platform 9 and the root portion 3 at the first end 32 and the second end 34 respectively.
  • the platform cooling device 10 includes the first protrusion 14 and the second protrusion 16. These protrusions 14, 16 form the cavity 30 extending from the first end 32 to the second end 34.
  • the cooling fluid 27 is directed via the inlet 18 into the platform cooling device 10 from a cooling fluid channel 26 in the root portion 3. More particularly, the inlet 18 is fluidly connected to the cooling fluid channel 26 in the root portion 3 for allowing the cooling fluid 27 to enter into the platform cooling device 10. The cooling fluid 27 is directed towards the plurality of impingement holes 20 via the channel 28.
  • the cavity 30 directs the cooling fluid 27 to flow towards the second end 34.
  • the second portion 12 of the platform cooling device 10 includes the plurality of dumping holes 22.
  • the dumping holes 22 are located proximal to the second end 34 beyond the inlet 18 as depicted in FIG. 3 .
  • the cooling fluid 27 after impinging against the platform 9 flows into the cavity 30 towards the plurality of dumping holes 22.
  • the dumping holes 22 direct the fluid out from the blade into the hot gas flow path.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12190755.4A 2012-10-31 2012-10-31 Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine Active EP2728114B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12190755.4A EP2728114B1 (de) 2012-10-31 2012-10-31 Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12190755.4A EP2728114B1 (de) 2012-10-31 2012-10-31 Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine

Publications (2)

Publication Number Publication Date
EP2728114A1 true EP2728114A1 (de) 2014-05-07
EP2728114B1 EP2728114B1 (de) 2016-02-10

Family

ID=47143638

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12190755.4A Active EP2728114B1 (de) 2012-10-31 2012-10-31 Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine

Country Status (1)

Country Link
EP (1) EP2728114B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160146016A1 (en) * 2014-11-24 2016-05-26 General Electric Company Rotor rim impingement cooling
EP3287596A1 (de) * 2016-08-25 2018-02-28 Siemens Aktiengesellschaft Plattformkühlungsvorrichtung für eine schaufel einer turbomaschine und turbomaschinenanordnung
CN109083685A (zh) * 2017-06-13 2018-12-25 通用电气公司 冷却布置和创建冷却布置的方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
EP1028228A1 (de) * 1999-02-10 2000-08-16 Siemens Aktiengesellschaft Kühlvorrichtung für Turbinenlaufschaufelplattform
US6120249A (en) 1994-10-31 2000-09-19 Siemens Westinghouse Power Corporation Gas turbine blade platform cooling concept
EP1413715A1 (de) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Prallkühlung der Plattform einer Gasturbinenlaufschaufel
CH703875A2 (de) * 2010-09-30 2012-03-30 Gen Electric Plattformkühlanordnung in einer Turbinenrotorschaufel sowie Verfahren zu deren Herstellung.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US6120249A (en) 1994-10-31 2000-09-19 Siemens Westinghouse Power Corporation Gas turbine blade platform cooling concept
EP1028228A1 (de) * 1999-02-10 2000-08-16 Siemens Aktiengesellschaft Kühlvorrichtung für Turbinenlaufschaufelplattform
EP1413715A1 (de) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Prallkühlung der Plattform einer Gasturbinenlaufschaufel
CH703875A2 (de) * 2010-09-30 2012-03-30 Gen Electric Plattformkühlanordnung in einer Turbinenrotorschaufel sowie Verfahren zu deren Herstellung.

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160146016A1 (en) * 2014-11-24 2016-05-26 General Electric Company Rotor rim impingement cooling
EP3287596A1 (de) * 2016-08-25 2018-02-28 Siemens Aktiengesellschaft Plattformkühlungsvorrichtung für eine schaufel einer turbomaschine und turbomaschinenanordnung
WO2018036719A1 (en) 2016-08-25 2018-03-01 Siemens Aktiengesellschaft A turbomachine arrangement with a platform cooling device for a blade of a turbomachine
CN109642464A (zh) * 2016-08-25 2019-04-16 西门子股份公司 具有用于涡轮机的动叶的平台冷却设备的涡轮机装置
US10895156B2 (en) * 2016-08-25 2021-01-19 Siemens Aktiengesellschaft Turbomachine arrangement with a platform cooling device for a blade of a turbomachine
CN109642464B (zh) * 2016-08-25 2021-10-22 西门子股份公司 具有用于涡轮机的动叶的平台冷却设备的涡轮机装置
CN109083685A (zh) * 2017-06-13 2018-12-25 通用电气公司 冷却布置和创建冷却布置的方法
EP3421165A1 (de) * 2017-06-13 2019-01-02 General Electric Company Verfahren zur erzeugung einer kühlanordnung in einer turbinkomponente ; turbinkomponente mit einer solchen kühlanordnung
JP2019023465A (ja) * 2017-06-13 2019-02-14 ゼネラル・エレクトリック・カンパニイ タービン構成要素のプラットフォーム冷却装置およびプラットフォーム冷却装置を作製する方法
CN109083685B (zh) * 2017-06-13 2023-08-29 通用电气公司 冷却布置和创建冷却布置的方法

Also Published As

Publication number Publication date
EP2728114B1 (de) 2016-02-10

Similar Documents

Publication Publication Date Title
JP6496499B2 (ja) タービンコンポーネントおよびそれを組立てる方法
US10895156B2 (en) Turbomachine arrangement with a platform cooling device for a blade of a turbomachine
EP3144479A1 (de) Statorkomponentenkühlung
EP3184742B1 (de) Turbinenschaufel mit hinterkantenkühlkreis
EP2607624B1 (de) Leitschaufel für eine Turbomaschine
JP2015178833A (ja) ターボ機械のロータブレードまたはガイドベーンの翼部分
CN107989659B (zh) 具有压力侧蛇形腔的部分包覆后缘冷却回路
EP2917494B1 (de) Schaufel für eine turbomaschine
CN108026779B (zh) 燃气轮机导向静叶节段及制造方法
EP3498973B1 (de) Schaufelblatt eines gasturbinentriebwerks und verfahren zur herstellung
JP2012132438A (ja) タービンロータブレードのプラットフォーム領域を冷却するための装置及び方法
EP2728114B1 (de) Plattformkühlungsvorrichtung für eine Schaufel einer Turbomaschine
JP2022510093A (ja) ターボ機械のブレード先端の取り付け
EP2946077B1 (de) Technik zum kühlen der fuss-seitenfläche einer plattform eines turbomaschinenteils
EP2752554A1 (de) Schaufel für eine Turbomaschine
JP2021501285A (ja) 先端トレンチ付きタービンブレード
JP2024014751A (ja) ステータベーンろう付継手の冷却回路
US11346246B2 (en) Brazed in heat transfer feature for cooled turbine components
JP2022505255A (ja) 翼形部クーポン取り付け
JP6854906B2 (ja) ターボ機械のための案内羽根

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: 20121031

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

17P Request for examination filed

Effective date: 20141107

RBV Designated contracting states (corrected)

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/18 20060101ALI20150630BHEP

Ipc: F01D 5/08 20060101AFI20150630BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150818

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): 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

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 774757

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160215

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012014642

Country of ref document: DE

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: 20160210

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 774757

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160210

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

Ref country code: ES

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

Effective date: 20160210

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: 20160510

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: 20160210

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: 20160511

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: 20160210

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: 20160210

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

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: 20160210

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: 20160210

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: 20160210

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: 20160210

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: 20160210

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: 20160610

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: 20160210

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: 20160210

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: 20160613

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

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

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: 20160210

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: 20160210

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012014642

Country of ref document: DE

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

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: 20160210

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: 20160210

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: 20160210

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: 20160210

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: BE

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: 20160210

26N No opposition filed

Effective date: 20161111

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

Ref country code: SI

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

Effective date: 20160210

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: 20160510

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: CH

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

Effective date: 20161031

Ref country code: LI

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

Effective date: 20161031

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: 20161031

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

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: 20161031

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

Ref country code: HU

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

Effective date: 20121031

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: 20160210

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: 20160210

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: 20160210

Ref country code: MT

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

Effective date: 20161031

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

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: 20160210

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: 20160210

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012014642

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: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20220901 AND 20220907

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

Ref country code: GB

Payment date: 20231024

Year of fee payment: 12

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: FR

Payment date: 20231026

Year of fee payment: 12

Ref country code: DE

Payment date: 20231027

Year of fee payment: 12