EP2354453B1 - Composant de moteur à turbine pour un refroidissement adaptatif - Google Patents

Composant de moteur à turbine pour un refroidissement adaptatif Download PDF

Info

Publication number
EP2354453B1
EP2354453B1 EP10152428.8A EP10152428A EP2354453B1 EP 2354453 B1 EP2354453 B1 EP 2354453B1 EP 10152428 A EP10152428 A EP 10152428A EP 2354453 B1 EP2354453 B1 EP 2354453B1
Authority
EP
European Patent Office
Prior art keywords
depression
turbine engine
body portion
back face
passage
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.)
Not-in-force
Application number
EP10152428.8A
Other languages
German (de)
English (en)
Other versions
EP2354453A1 (fr
Inventor
Andrew Shepherd
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 EP10152428.8A priority Critical patent/EP2354453B1/fr
Priority to US13/017,350 priority patent/US20110189015A1/en
Publication of EP2354453A1 publication Critical patent/EP2354453A1/fr
Application granted granted Critical
Publication of EP2354453B1 publication Critical patent/EP2354453B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life

Definitions

  • the present invention seeks to find a solution in which the time of operation can be stretched further and downtime may be avoided even when oxidation of parts has already occurred, so that repair or replacement of parts can be performed at the next maintenance schedule and still providing a mode of operation with only marginal performance losses.
  • a turbine engine component having a body comprising a first surface exposed to a working fluid of high temperatures during operation, so that erosion and/or corrosion, e.g. particularly oxidation, may take place on the first surface.
  • the body is further comprising a second surface comprising at least one depression, the depression being exposed to a cooling fluid during operation, the depression being oriented such that, starting from the second surface, it deepens in direction of a back face of the first surface.
  • a depression may be in form of a blind hole or a trench.
  • the body also comprises a body portion between the back face and the first surface, wherein a diameter of the depression decreases from the second surface in direction of the back face.
  • the depression can be seen as to have a particularly V-shaped cross section.
  • the invention is not directed to oxidise surfaces of cooling passages. It is directed to scenarios in which a hot surface that is designed to guide the hot fluid - the first surface according to the invention - may oxidise.
  • the depression has a specific shape, so that the diameter of the depression decreases from the second surface in direction of the back face of the first surface.
  • this passage has an exit with a first diameter, as defined by the width of the depression, providing a first amount of cooling fluid. This will stop or slow down further oxidation in the future. Assuming, oxidation will not be prevented completely because the first amount of cooling fluid may not be sufficient to do so, the first surface including the rim of the newly built passage may oxidise further. This results in a further gradual reduction of surface material and also in enlarging the diameter of the cooling passage, due to the specific shape of the depression with its tilted walls.
  • the invention is advantageous because, if the heat will never reach an oxidising temperature, the depression will never become a cooling passage and therefore no performance losses will occur.
  • the aerofoil 1 for example a guide vane or a blade within a turbine section of a gas turbine engine, represents the turbine engine component as defined in the invention and will be present in a working fluid flow 30 during operation.
  • This working fluid flow 30 is indicated as a double arrow and may be a hot gas provided by a combustion chamber located upstream.
  • the aerofoil 1 has a circumferential wall 2 as a body of turbine engine component and a cavity to allow cooling fluid - a cooling fluid flow 31 is indicated via a further arrow - to cool the wall 2 from the inside and to supply cooling holes (not shown in the figure).
  • the depressions 20, 21 are being exposed to the cooling fluid during operation. At the time of installation, the depressions 20, 21 are blind holes and may not supply any cooling fluid to the first surface 10.
  • the first depression 20 has an opening of the first diameter d1 then narrows until the back face 12 is reached with a diameter of the second diameter d2.
  • the width of the material of the body portion 40 is indicated by the width w and may be a fraction of a width of a medium distance between the first surface 10 and the second surface 11.
  • the material degradation of the first surface 10 may continue at a slower pace. This result in further oxidisation, as indicated by a dashed line for a further oxidised first surface 14.
  • the height of the passages 50 will also decrease, which has a direct impact on the width of the passage 50, due to the tilted walls of the passage 50.
  • the throughput of cooling air will increase through the passage 50, because the second diameter d2 indicating the diameter of the passage exit will also increase. This has the consequence that the oxidisation of the first surface 10 will decrease further until a stable point of operation is reached, at which enough cooling air is provided via the passage 50.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Composant de moteur à turbine (1), en particulier une pale, présentant un corps (2) comprenant :
    - une première surface (10) exposée à un fluide de fonctionnement atteignant des températures élevées en cours de fonctionnement ;
    - une deuxième surface (11) comprenant au moins une dépression (20, 21, 22, 23, 24, 25, 26), la dépression (20, 21,...) étant exposée à un liquide de refroidissement en cours de fonctionnement, la dépression (20, 21,...) étant orientée de telle manière que, en partant de la deuxième surface (11), elle se creuse en direction d'une face arrière (12) de la première surface (10) ;
    - une partie corps (40) entre la face arrière (12) et la première surface (10) ;
    dans lequel un diamètre (d1, d2) de la dépression (20, 21...) diminue à partir de la deuxième surface (11) en direction de la face arrière (12),
    caractérisé en ce que
    la partie corps (40) est constituée d'un matériau et/ou présente une largeur (w) entre la première surface (10) et la face arrière (12) de la première surface (10) tel(le) que, en cours d'utilisation et en cas d'exposition à une température spécifique, une érosion et/ou une corrosion sur le côté première surface (10) de la partie corps (40) va pratiquer un passage (50) vers la dépression (20, 21,...),
    et le diamètre (d1, d2) de la dépression (20, 21,...) diminue à partir de la deuxième surface (11) en direction de la face arrière (12) de telle manière que, en cours d'utilisation, une érosion et/ou une corrosion continue sur le côté première surface (10) de la partie corps (40) a pour conséquence un élargissement du passage (50) afin de laisser passer une quantité supérieure de liquide de refroidissement.
  2. Composant de moteur à turbine (1) selon la revendication 1,
    caractérisé en ce que
    une partie du corps (12) adjacente à la partie corps (40) est constituée d'un autre matériau qui est moins susceptible d'érosion et/ou de corrosion que la partie corps (40).
  3. Composant de moteur à turbine (1) selon la revendication 2,
    caractérisé en ce que
    l'autre matériau est un revêtement résistant à l'oxydation (60) .
  4. Composant de moteur à turbine (1) selon l'une quelconque des revendications 1 à 3,
    caractérisé en ce que
    le passage pratiqué (50) fournit le liquide de refroidissement afin de provoquer un refroidissement, en particulier un refroidissement pelliculaire, d'une proximité de la première surface (10).
  5. Composant de moteur à turbine (1) selon la revendication 4,
    caractérisé en ce que
    le diamètre (d1, d2) de la dépression (20, 21,..) diminue à partir de la deuxième surface (11) en direction de la face arrière (12) de sorte que, en cours d'utilisation, un élargissement continu du passage (50) en raison de l'érosion et/ou de la corrosion fournit une quantité croissante de liquide de refroidissement traversant de sorte que la température d'une proximité de la première surface (10) est réduite jusqu'à une valeur pour laquelle l'érosion et/ou la corrosion sur le côté première surface (10) de la partie corps (40) s'interrompt.
  6. Moteur à turbine à gaz, comprenant :
    au moins un composant de moteur à turbine (1) selon l'une quelconque des revendications précédentes.
  7. Moteur à turbine à gaz selon la revendication 6,
    caractérisé en ce que
    le au moins un composant de moteur à turbine (1) fait partie de :
    - une pale d'aube, et/ou
    - une plateforme d'aube, et/ou
    - une pale d'ailette, et/ou
    - une plateforme d'ailette, et/ou
    - un carénage d'ailette, et/ou
    - une conduite de transition entre une chambre de combustion et une section de turbine, et/ou
    - une chambre de combustion, et/ou
    - un carénage statique, et/ou
    - un bouclier thermique, et/ou
    - un diffuseur, et/ou
    - un échappement.
  8. Procédé de refroidissement adaptatif d'un composant de moteur à turbine (1), le procédé comprenant les étapes consistant à :
    - fournir un liquide de refroidissement au composant de moteur à turbine (1) présentant un corps comprenant une première surface (10) exposée à un fluide de fonctionnement atteignant des températures élevées en cours de fonctionnement, une deuxième surface (11) comprenant une dépression (20, 21, 22, 23, 24, 25, 26), la dépression (20, 21,...) étant exposée au liquide de refroidissement en cours de fonctionnement, la dépression (20, 21,...) étant orientée de telle manière que, en partant de la deuxième surface (11), elle se creuse en direction d'une face arrière (12) de la première surface (10), et comprenant également une partie corps (40) entre la face arrière (12) et la première surface (10), dans lequel un diamètre (d1, d2) de la dépression (20, 21,...) diminue à partir de la deuxième surface (11) en direction de la face arrière (12) ;
    - appliquer de la chaleur à la première surface (10) de sorte que de la matière de la première surface (10) est érodée et/ou corrodée sur le côté première surface (10) de la partie corps (40) de sorte qu'un passage (50) vers la dépression (20, 21,...) sera pratiqué pour permettre au liquide de refroidissement de passer, et de sorte qu'une érosion et/ou une corrosion continue sur le côté première surface (10) de la partie corps (40) a pour conséquence un élargissement du passage (50) afin de laisser passer une quantité supérieure de liquide de refroidissement.
EP10152428.8A 2010-02-02 2010-02-02 Composant de moteur à turbine pour un refroidissement adaptatif Not-in-force EP2354453B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10152428.8A EP2354453B1 (fr) 2010-02-02 2010-02-02 Composant de moteur à turbine pour un refroidissement adaptatif
US13/017,350 US20110189015A1 (en) 2010-02-02 2011-01-31 turbine engine component for adaptive cooling

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10152428.8A EP2354453B1 (fr) 2010-02-02 2010-02-02 Composant de moteur à turbine pour un refroidissement adaptatif

Publications (2)

Publication Number Publication Date
EP2354453A1 EP2354453A1 (fr) 2011-08-10
EP2354453B1 true EP2354453B1 (fr) 2018-03-28

Family

ID=42289328

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10152428.8A Not-in-force EP2354453B1 (fr) 2010-02-02 2010-02-02 Composant de moteur à turbine pour un refroidissement adaptatif

Country Status (2)

Country Link
US (1) US20110189015A1 (fr)
EP (1) EP2354453B1 (fr)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9435208B2 (en) 2012-04-17 2016-09-06 General Electric Company Components with microchannel cooling
US9617859B2 (en) * 2012-10-05 2017-04-11 General Electric Company Turbine components with passive cooling pathways
US10006367B2 (en) * 2013-03-15 2018-06-26 United Technologies Corporation Self-opening cooling passages for a gas turbine engine
US9394798B2 (en) * 2013-04-02 2016-07-19 Honeywell International Inc. Gas turbine engines with turbine airfoil cooling
JP6227653B2 (ja) * 2013-07-30 2017-11-08 三菱日立パワーシステムズ株式会社 蒸気タービンの水分除去装置、及びスリット孔の形成方法
EP2857636A1 (fr) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Agencement de refroidissement amélioré pour composant de turbomachine
EP2873806A1 (fr) * 2013-11-14 2015-05-20 Siemens Aktiengesellschaft Revêtement barrière thermique amélioré de système de refroidissement pour un composant de turbomachine
US9784123B2 (en) 2014-01-10 2017-10-10 Genearl Electric Company Turbine components with bi-material adaptive cooling pathways
EP2937512B1 (fr) * 2014-04-23 2020-05-27 United Technologies Corporation Agencement pour un moteur à turbine à gaz
DE102014207790A1 (de) * 2014-04-25 2015-10-29 Siemens Aktiengesellschaft Kühlfluidkanal
US9718735B2 (en) * 2015-02-03 2017-08-01 General Electric Company CMC turbine components and methods of forming CMC turbine components
US10738622B2 (en) 2016-08-09 2020-08-11 General Electric Company Components having outer wall recesses for impingement cooling
US10662779B2 (en) * 2016-11-17 2020-05-26 Raytheon Technologies Corporation Gas turbine engine component with degradation cooling scheme
US10508553B2 (en) 2016-12-02 2019-12-17 General Electric Company Components having separable outer wall plugs for modulated film cooling
US10927680B2 (en) * 2017-05-31 2021-02-23 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US10704399B2 (en) * 2017-05-31 2020-07-07 General Electric Company Adaptively opening cooling pathway
US10760430B2 (en) * 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US11041389B2 (en) * 2017-05-31 2021-06-22 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US20180347442A1 (en) * 2017-05-31 2018-12-06 General Electric Company Lattice structure in cooling pathway by additive manufacture
KR102230700B1 (ko) * 2017-09-12 2021-03-23 한국기계연구원 가스 터빈용 블레이드
US11352886B2 (en) 2017-10-13 2022-06-07 General Electric Company Coated components having adaptive cooling openings and methods of making the same
JP7214831B2 (ja) 2018-07-31 2023-01-30 ゼネラル・エレクトリック・カンパニイ 適応冷却を組み込んだ機械的ロック機構を備えたコンポーネントおよび製造方法
US11203939B2 (en) * 2018-12-12 2021-12-21 Raytheon Technologies Corporation Airfoil platform with cooling orifices
US11248790B2 (en) 2019-04-18 2022-02-15 Rolls-Royce Corporation Impingement cooling dust pocket
US11333037B2 (en) 2020-02-06 2022-05-17 Raytheon Technologies Corporation Vane arc segment load path

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090074576A1 (en) * 2006-04-20 2009-03-19 Florida Turbine Technologies, Inc. Turbine blade with cooling breakout passages

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1492049A (en) 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4136516A (en) 1977-06-03 1979-01-30 General Electric Company Gas turbine with secondary cooling means
IE861475L (en) * 1985-07-03 1987-01-03 Tsnii Kozhevenno Obuvnoi Ptomy Improved coolant passage structure especially for cast rotor¹blades in a combustion turbine
DE3615226A1 (de) * 1986-05-06 1987-11-12 Mtu Muenchen Gmbh Heissgasueberhitzungsschutzeinrichtung fuer gasturbinentriebwerke
GB2259118B (en) 1991-08-24 1995-06-21 Rolls Royce Plc Aerofoil cooling
JP2000517397A (ja) * 1996-09-04 2000-12-26 シーメンス アクチエンゲゼルシヤフト 高温ガス流に曝されるタービン翼
DE60042061D1 (de) * 2000-05-31 2009-06-04 Alstom Technology Ltd Verfahren zum Einstellen der Grösse von Kühllöchern eines Bauteils einer Gasturbine
US6749396B2 (en) * 2002-06-17 2004-06-15 General Electric Company Failsafe film cooled wall
DE10250779A1 (de) 2002-10-30 2004-05-19 Alstom (Switzerland) Ltd. Notkühlsystem für ein hitzebelastetes Bauteil
FR2870560B1 (fr) * 2004-05-18 2006-08-25 Snecma Moteurs Sa Circuit de refroidissement a cavite a rapport de forme eleve pour aube de turbine a gaz
US7186091B2 (en) * 2004-11-09 2007-03-06 General Electric Company Methods and apparatus for cooling gas turbine engine components
US7241107B2 (en) * 2005-05-19 2007-07-10 Spanks Jr William A Gas turbine airfoil with adjustable cooling air flow passages
GB2429515B (en) 2005-08-11 2008-06-25 Rolls Royce Plc Cooling method and apparatus

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090074576A1 (en) * 2006-04-20 2009-03-19 Florida Turbine Technologies, Inc. Turbine blade with cooling breakout passages

Also Published As

Publication number Publication date
EP2354453A1 (fr) 2011-08-10
US20110189015A1 (en) 2011-08-04

Similar Documents

Publication Publication Date Title
EP2354453B1 (fr) Composant de moteur à turbine pour un refroidissement adaptatif
EP2860359B1 (fr) Dispositif de refroidissement d'un composant dans le trajet de gaz chauds d'une turbine à gaz
EP2365188B1 (fr) Refroidissement de composants de turbine à gaz comprenant des canaux dans les rainures de joints
US8434692B2 (en) Flow distribution regulation arrangement with bimetallic elements for adjusting the flow distribution in a cooling channel
EP2607624B1 (fr) Aube statorique pour turbomachine
US20090074576A1 (en) Turbine blade with cooling breakout passages
US20100124485A1 (en) Aerofoil cooling arrangement
EP2159376A2 (fr) Manchon pour aube de turbomachine et procédé de refroidissement d'une aube
JP4250088B2 (ja) ガスタービン動翼或いは静翼の衝突冷却構造
JP2008075644A (ja) タービンエンジン用の翼形部バケット
JP4890142B2 (ja) 冷却式シュラウド組立体及びシュラウドの冷却方法
EP3168535B1 (fr) Corps de forme aérodynamique et procédé de refroidissement d'un corps placé dans un écoulement de fluide chaud
EP3090145B1 (fr) Turbulateur de passage de refroidissement de composant de turbine à gaz
EP3406852B1 (fr) Composant de turbine à refroidissement de film d'extrémité et procédé de refroidissement
JP5443600B2 (ja) ターボ機械のための環状流路
AU2008303598A1 (en) Gas turbine having welded combustion chamber shells
WO2015071141A1 (fr) Agencement de refroidissement amélioré à revêtement de barrière thermique pour composant de turbomachine
JP4202038B2 (ja) タービンノズル及びシュラウドを選択的に配置する方法及びガスタービン
JP2014148938A (ja) ターボ機械のためのフィルム冷却されるタービンブレード
KR20190083974A (ko) 캡 요소를 갖는 터빈 구성요소를 위한 냉각 통로를 형성하는 방법
EP3421721A1 (fr) Composant de turbomachine et procédé de fabrication d'un composant de turbomachine
EP3933172B1 (fr) Trou de diffuseur de refroidissement pelliculaire
JP2021127764A (ja) 後端排気導管および後端フランジを含む高温ガス経路構成要素

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

AK Designated contracting states

Kind code of ref document: A1

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

17P Request for examination filed

Effective date: 20120210

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

17Q First examination report despatched

Effective date: 20160307

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

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: 20171018

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): 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 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: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 983638

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180415

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: 602010049449

Country of ref document: DE

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: 20180328

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: 20180328

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: 20180328

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: 20180628

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180328

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: 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: 20180629

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: 20180628

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

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: 20180328

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 983638

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180328

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

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: 20180730

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602010049449

Country of ref document: DE

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: 20180328

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: 20180328

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: 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: 20180328

26N No opposition filed

Effective date: 20190103

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: 20180328

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20190202

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: 20180328

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190228

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: LI

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

Effective date: 20190228

Ref country code: CH

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

Effective date: 20190228

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: 20190202

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: 20190228

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: 20180328

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

Ref country code: MT

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

Effective date: 20190202

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

Ref country code: DE

Payment date: 20200420

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602010049449

Country of ref document: DE

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

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

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

Ref country code: FR

Payment date: 20210215

Year of fee payment: 12

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

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: 20180328

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

Ref country code: GB

Payment date: 20210302

Year of fee payment: 12

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: 20180728

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: 20100202

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602010049449

Country of ref document: DE

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: 20210901

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: 20180328

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

Effective date: 20220202

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: 20220228

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: 20220202