EP1757773B1 - Aube creuse de turbine - Google Patents

Aube creuse de turbine Download PDF

Info

Publication number
EP1757773B1
EP1757773B1 EP05018595A EP05018595A EP1757773B1 EP 1757773 B1 EP1757773 B1 EP 1757773B1 EP 05018595 A EP05018595 A EP 05018595A EP 05018595 A EP05018595 A EP 05018595A EP 1757773 B1 EP1757773 B1 EP 1757773B1
Authority
EP
European Patent Office
Prior art keywords
profile
turbine blade
slot
profile wall
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.)
Not-in-force
Application number
EP05018595A
Other languages
German (de)
English (en)
Other versions
EP1757773A1 (fr
Inventor
Fathi Ahmad
Michael Dr. Dankert
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 DE502005003344T priority Critical patent/DE502005003344D1/de
Priority to EP05018595A priority patent/EP1757773B1/fr
Priority to ES05018595T priority patent/ES2303163T3/es
Priority to CNA2006101463720A priority patent/CN1936273A/zh
Priority to US11/510,239 priority patent/US7845905B2/en
Priority to JP2006228883A priority patent/JP4689558B2/ja
Publication of EP1757773A1 publication Critical patent/EP1757773A1/fr
Application granted granted Critical
Publication of EP1757773B1 publication Critical patent/EP1757773B1/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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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

Definitions

  • the invention relates to a hollow turbine blade with an airfoil profile formed by a suction-side profile wall and a pressure-side profile wall and having a profile height directed along a blade axis from a platform to a profile tip, with at least one support rib provided in the interior of the turbine blade which connects the pressure-side profile wall with the suction-side profile wall in each case in a connection region and with at least one slot provided in the profile wall on the hot gas side and extending along the blade axis. Furthermore, the invention relates to the use of a generic turbine blade.
  • the object of the invention is therefore to provide a turbine blade with extended life.
  • the object is achieved by a generic turbine blade in which the slot opposite hot gas side in the profile wall of the connecting rib formed by the support rib and the profile wall.
  • the invention is based on the recognition that the material of the airfoil profile heats up due to the outside flowing hot gas.
  • the extending between the pressure-side profile wall and the suction-side profile wall inside support rib is colder than the heated material of the profile walls.
  • the support rib merges integrally into the pressure-side or suction-side profile wall, heat energy is locally conducted from the respective profile wall into the support rib via the inner connection region and dissipated, so that a reduced material temperature along the overflow in the profile wall in the mouth region of the support rib Profile height extending connection area occurs.
  • the profile wall is hotter in many areas. As a result, thermal stresses occur in the material, which can cause crack generation and promote crack growth.
  • the invention proposes that the slot opposite the hot gas side in the profile wall of the connecting rib formed by the support rib and the profile wall.
  • the slot relieves the material by allowing locally larger thermal expansion of the profile wall.
  • the relief slot leads to a life-prolonging reduction of the thermally induced stresses in the profile wall.
  • the thermal stresses still occurring in the airfoil then occur in an order of magnitude that is harmless to the material. Cracks and / or crack growth are less likely to occur at this point, extending the life of the turbine blade.
  • the slot can also serve as a crack stopper or
  • Crack limiter serve, which in turn can extend the life of the turbine blade.
  • a gas turbine equipped with this long-life turbine blade has a longer operating time and a shorter service life, since the turbine blades are less likely to be examined for cracks with critical lengths and replaced if necessary.
  • the maintenance costs of gas turbines can be lowered and their cost-effectiveness can be further improved.
  • the slot extends along the blade axis and has at least a length of 10%, preferably at least 20% of the profile height.
  • this measure extends the service life of the gas turbine, since the support ribs provided in the interior of the turbine blade also extend along the blade axis and connect the pressure-side profile wall with the suction-side profile wall in each case in a connection region.
  • the slot or slits may also extend into the transition region.
  • the transition region can be protected from cracking.
  • crack propagation is delayed or limited in the transition region.
  • the slot provided in the hot gas-circumscribed outer surface can also extend beyond the transition region into the platform.
  • the locally occurring cold entry ie the heat extraction locally occurring due to the cooler support rib
  • the locally occurring cold entry can be lowered in a particularly effective manner, whereby the material of the profile wall, between the connection region and the outer surface opposite thereto, in comparison to The state of the art is warmer.
  • the thermal stresses are reduced, which leads to an extension of the service life of the turbine blade.
  • the slot is filled with a filler material to avoid possibly occurring aerodynamic losses in the hot gas due to edges.
  • the filling material is softer than the material of the profile wall. The occurring thermally induced strains of the profile wall can be compensated particularly well in this case of the soft filler.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17, which with a annular hot gas channel 18 communicates.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • vanes 13 As seen in the flow direction of a hot gas 11 produced in the annular combustion chamber 6, follows in the hot gas channel 18 in each case one row of vanes 13 a row 14 formed of blades 15.
  • the vanes 12 are attached to the stator, whereas the blades 15 a row 14 mounted by a turbine disk on the rotor 3 are.
  • a generator or a working machine (not shown) is coupled.
  • FIG. 2 shows a turbine blade 30 according to the invention in a perspective view.
  • the turbine blade 30 has a platform 32, on the surface 34 of which a hot air 11 umströmbares airfoil 36 is arranged.
  • the airfoil 36 extends from a leading edge 38 to a trailing edge 40. It also has an intake side profile wall 42 extending therebetween and a pressure side profile wall 44 also extending therebetween.
  • three cavities 46 are provided, which are separated from each other by two support ribs 48.
  • the support ribs 48 connect the suction-side profile wall 42 with the pressure-side profile wall 44 and serve to increase the rigidity of the airfoil profile 36.
  • the turbine blade 30 is typically manufactured by a casting process. In a casting apparatus three casting cores are used for this purpose, which are removed after the manufacture of the turbine blade 30 from this. At this point, the cavities remain 46, between which the support ribs 48 are arranged. Therefore, with cast turbine blade 30, the support ribs 48 integrally merge into and interconnect with the suction and / or pressure side profile walls 42, 44 in a connection region 50, providing particularly good thermal coupling of the profile wall 42, 44 to the support rib.
  • the airfoil 36 surrounded by the hot gas 11 is completely heated.
  • a temperature profile has hitherto formed which has a local temperature minimum in the region of each support rib 48. This caused by the cooler support rib 48 uneven heating of the airfoil profile 36 caused in the near-surface portion of the profile walls 42, 44 so large, thermally induced stresses that there cracks could occur and crack growth occurred more. This limited the life of the known turbine blade.
  • the slot 56 provided in a profile wall 42, 44 is now arranged in a section of the profile wall 42, 44 which corresponds to the connection area 50 and thus also the support rib 48 is opposite.
  • the slot 56 raises the local temperature minimum occurring in its area since the thermal conductivity of the connection area 50 has been reduced due to the reduced cross-section. Accordingly, the temperature gradients along the tread walls 42, 44 are reduced from the leading edge 38 to the trailing edge 40, which reduces stress in the portion having the slot 50. The thermal stresses are then at a harmless level and the material of the airfoil 36 can thereby withstand the loads occurring longer.
  • the slots 56 have a minimum length L, which corresponds to at least 10%, preferably at least 20% of the height H of the airfoil 36.
  • the height H of the airfoil 36 is determined between the surface 34 of the platform 32 and the apex 58 of the airfoil 36.
  • the slot 56 can extend into a rounded transition region 60, which is arranged between the platform 32 and the airfoil profile 36.
  • This configuration of the slots 56 is represented by the contours 62 shown in dashed line style.
  • a particularly good protection against crack-like wear can be achieved if the slot 62 also extends into the platform 32.
  • FIG. 3 shows a section through the turbine blade 30 according to the invention along the section line III FIG. 2 ,
  • the turbine blade 30 can be designed both as a moving blade and / or as a guide blade for a particular stationary gas turbine 1.
  • the airfoil profile 36 shown in cross-section shows the leading edge 38, the trailing edge 40, the suction-side profile wall 42, the pressure-side profile wall 44 and two support ribs 48 separating the cavities 46 which merge into the profile walls 42, 44 in a connection region 50.
  • the slots shown 56 are filled with a filler, whereby a particular aerodynamic surface contour of the airfoil 36 can bring about. Transverse to the flow direction of the hot gas 11 extending projections and edges are thereby avoided in the profile walls 42, 44.
  • the slots 56 each protrude into the profile walls 42, 44 with a penetration depth E. This can be so large that the slots 56 protrude into the connection region 50 and possibly even beyond it into the support ribs 48. This ensures that the temperature difference along the airfoil profile 36 from the leading edge 38 to the trailing edge 48 is made particularly effective, so as to further increase the life of the turbine blade 30.
  • the invention is particularly effective when the hollow turbine blade 30 and the airfoil profile 36 are flowed through by a coolant, for example compressor air taken from the compressor 5 of the gas turbine 1.
  • a coolant for example compressor air taken from the compressor 5 of the gas turbine 1.
  • the profile walls 42, 44 are cooled from the inside, as well as the support ribs 48.
  • the unwanted local cold entry or the local heat removal from the profile wall 42, 44 via the connecting portion 50 and the support ribs 48 is due to the particularly good thermoelectric coupling particularly effective. Accordingly, the temperature differences along the profile walls 42, 44 and thus also the thermal stresses in an internally cooled turbine blade 30 are particularly large.
  • the life, in particular of internally cooled turbine blades 30 can be extended particularly effective with the invention.
  • the serving for thermal relief slots 56 may also be provided in only one profile wall, for example, the suction-side profile wall 42 or the pressure-side profile wall 44.
  • the slots 56, 62 serve as boundaries for cracks occurring in the adjacent blade material. For example, if in the region of the central cavity 46 in one of the two profile walls 42, 44, a crack is present and this lengthens in the flow direction of the hot gas 11, this forcibly increased to a maximum of one of the two slots 56. The extension of the crack on the slot 56 is not possible.
  • the invention provides a measure for equalizing the thermal stress in a wing profile 36 of a turbine blade 30 in order to increase the service life of the turbine blade 30 and, accordingly, the operating times of a gas turbine 1 equipped therewith.
  • the invention proposes that the hollow turbine blade 30 in the region of the support ribs 48, which has a suction-side profile wall 42 with a pressure-side profile wall 44 in each case connect a connecting portion 50 together, has hot gas side arranged slots 56 for relief.

Landscapes

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

Claims (8)

  1. Aube (30) creuse de turbine,
    ayant un profil (36) d'aile portante formé par une paroi (42) de profil du côté de l'extrados et par une paroi (44) de profil du côté de l'intrados et autour duquel passe un gaz (11) chaud, profil qui a, d'une plateforme (32) jusqu'à une pointe (58) de profil, une hauteur (H) de profil dirigée le long d'un axe d'aube,
    comprenant au moins une barre (48) d'appui, qui est prévue à l'intérieur de l'aube (30) de turbine et qui relie la paroi (44) de profil du côté de l'extrados à la paroi (42) de profil du côté de l'intrados dans respectivement une partie (50) de liaison, et
    comprenant au moins une fente (56) prévue du côté du gaz chaud dans la paroi (42, 44) de profil,
    caractérisée
    en ce que la fente (56) du côté du gaz chaud dans la paroi (42, 44) de profil est opposée à la partie (50) de liaison formée par la barre (48) d'appui et par la paroi (42, 44) de profil.
  2. Aube (30) de turbine suivant la revendication 1,
    dans laquelle la fente (56) s'étend le long de l'axe de l'aube et a au moins une longueur représentant 10 % et de préférence représentant au moins 20 % de la hauteur (H) du profil.
  3. Aube (30) de turbine suivant la revendication 1 ou 2,
    dans laquelle il est prévu entre la plateforme (32) et le profil (36) de surface portante une partie (60) de transition arrondie, dans laquelle s'étend la fente (56).
  4. Aube (30) de turbine suivant la revendication 3,
    dans laquelle la fente (56) s'étend dans la plateforme (32).
  5. Aube (30) de turbine suivant l'une des revendications 1 à 4,
    dans laquelle la fente (56) a une profondeur (E) de pénétration, qui va jusque dans la partie (50) de liaison et/ou dans la barre (48) d'appui.
  6. Aube (30) de turbine suivant l'une des revendications 1 à 5,
    dans laquelle la fente (56) est remplie d'une matière de remplissage;
  7. Aube (30) de turbine suivant la revendication 6,
    Dans laquelle la matière de remplissage est plus tendre que la matière de la paroi (42, 44) du profil.
  8. Aube (30) de turbine refroidie suivant l'une des revendications précédentes.
EP05018595A 2005-08-26 2005-08-26 Aube creuse de turbine Not-in-force EP1757773B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE502005003344T DE502005003344D1 (de) 2005-08-26 2005-08-26 Hohle Turbinenschaufel
EP05018595A EP1757773B1 (fr) 2005-08-26 2005-08-26 Aube creuse de turbine
ES05018595T ES2303163T3 (es) 2005-08-26 2005-08-26 Alabe de turbina hueco.
CNA2006101463720A CN1936273A (zh) 2005-08-26 2006-08-25 空心透平叶片
US11/510,239 US7845905B2 (en) 2005-08-26 2006-08-25 Hollow turbine blade
JP2006228883A JP4689558B2 (ja) 2005-08-26 2006-08-25 中空タービン翼

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05018595A EP1757773B1 (fr) 2005-08-26 2005-08-26 Aube creuse de turbine

Publications (2)

Publication Number Publication Date
EP1757773A1 EP1757773A1 (fr) 2007-02-28
EP1757773B1 true EP1757773B1 (fr) 2008-03-19

Family

ID=36584564

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05018595A Not-in-force EP1757773B1 (fr) 2005-08-26 2005-08-26 Aube creuse de turbine

Country Status (6)

Country Link
US (1) US7845905B2 (fr)
EP (1) EP1757773B1 (fr)
JP (1) JP4689558B2 (fr)
CN (1) CN1936273A (fr)
DE (1) DE502005003344D1 (fr)
ES (1) ES2303163T3 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2322661T3 (es) * 2006-08-23 2009-06-24 Siemens Aktiengesellschaft Alabe de turbina recubierto.
US8500411B2 (en) * 2010-06-07 2013-08-06 Siemens Energy, Inc. Turbine airfoil with outer wall thickness indicators
EP2863010A1 (fr) * 2013-10-21 2015-04-22 Siemens Aktiengesellschaft Aube de turbine
CN104006000A (zh) * 2014-05-29 2014-08-27 安徽银龙泵阀股份有限公司 一种内置冷却管的泵芯
EP2990598A1 (fr) * 2014-08-27 2016-03-02 Siemens Aktiengesellschaft Aube de turbine et turbine
EP2998507A1 (fr) 2014-09-16 2016-03-23 Siemens Aktiengesellschaft Une aube de turbine refroidie comportant des entretoises internes entre les cavités de refroidissement qui comportent des points de rupture pour reduir les gradients thermiques
CN104747241A (zh) * 2015-01-23 2015-07-01 朱晓义 一种压力装置及涡轮发动机
US20170328206A1 (en) * 2016-05-16 2017-11-16 United Technologies Corporation Method and Apparatus to Enhance Laminar Flow for Gas Turbine Engine Components
US10731469B2 (en) * 2016-05-16 2020-08-04 Raytheon Technologies Corporation Method and apparatus to enhance laminar flow for gas turbine engine components
US20180051566A1 (en) * 2016-08-16 2018-02-22 General Electric Company Airfoil for a turbine engine with a porous tip
CN106703897B (zh) * 2016-12-21 2018-01-12 中国南方航空工业(集团)有限公司 一种空心叶片内腔低熔点合金清理装置
CN106761953B (zh) * 2016-12-21 2018-05-08 中国南方航空工业(集团)有限公司 一种叶片内腔低熔点合金去除装置
CN106757044B (zh) * 2016-12-21 2018-12-14 中国南方航空工业(集团)有限公司 一种空心叶片内腔低熔点合金清理方法
CN106757045B (zh) * 2016-12-21 2018-12-14 中国南方航空工业(集团)有限公司 一种叶片内腔低熔点合金去除方法
DE102017208707A1 (de) 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Turbinenschaufel
DE102017218886A1 (de) 2017-10-23 2019-04-25 MTU Aero Engines AG Schaufel und Rotor für eine Strömungsmaschine sowie Strömungsmaschine
US11118462B2 (en) 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
JP6799702B1 (ja) * 2020-03-19 2020-12-16 三菱パワー株式会社 静翼及びガスタービン
US11371359B2 (en) 2020-11-26 2022-06-28 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2807870A (en) * 1952-02-05 1957-10-01 Gen Motors Corp Method of making a propeller blade
US2882974A (en) * 1954-04-28 1959-04-21 Gen Motors Corp Propeller blade
US2933286A (en) * 1954-09-15 1960-04-19 Gen Electric Damping turbine buckets
US3290004A (en) * 1965-04-09 1966-12-06 Hitachi Ltd Device for damping vibration of long steam-turbine blades
US5690473A (en) * 1992-08-25 1997-11-25 General Electric Company Turbine blade having transpiration strip cooling and method of manufacture
JPH1061406A (ja) * 1996-08-27 1998-03-03 Mitsubishi Heavy Ind Ltd ガスタービン翼の冷却構造
JP3971009B2 (ja) * 1998-01-28 2007-09-05 Ｊｕｋｉ会津株式会社 ドレン穴付きノズル翼の製造方法
JP2000001801A (ja) 1998-06-13 2000-01-07 Sanwa:Kk 古紙を含んだコンクリート枕木又はコンクリートブロ ック又はコンクリートｕ字溝
JP2000018001A (ja) * 1998-06-30 2000-01-18 Mitsubishi Heavy Ind Ltd 動翼熱応力軽減装置
EP1508399B1 (fr) 2003-08-22 2006-12-27 Siemens Aktiengesellschaft Aube de turbomachine et procédé pour empêcher la propagation des fissures dans une aube de turbomachine
DE50306044D1 (de) * 2003-09-05 2007-02-01 Siemens Ag Schaufel einer Turbine
EP1525942A1 (fr) * 2003-10-23 2005-04-27 Siemens Aktiengesellschaft Turbine à gas et aube mobile pour turbomachine
US7318699B2 (en) * 2005-05-31 2008-01-15 General Electric Company Moisture removal grooves on steam turbine buckets and covers and methods of manufacture

Also Published As

Publication number Publication date
JP4689558B2 (ja) 2011-05-25
DE502005003344D1 (de) 2008-04-30
US7845905B2 (en) 2010-12-07
JP2007064219A (ja) 2007-03-15
US20070128035A1 (en) 2007-06-07
ES2303163T3 (es) 2008-08-01
CN1936273A (zh) 2007-03-28
EP1757773A1 (fr) 2007-02-28

Similar Documents

Publication Publication Date Title
EP1757773B1 (fr) Aube creuse de turbine
EP1907670B1 (fr) Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
DE60018817T2 (de) Gekühlte Gasturbinenschaufel
EP1834066B1 (fr) Aube de turbine pour turbine a gaz, utilisation d'une aube de turbine et procede de refroidissement d'une aube de turbine
EP1512489B1 (fr) Aube pour turbine
DE3019920C2 (de) Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke
EP1766192B1 (fr) Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
EP2059655B1 (fr) Aube mobile refroidie pour turbines
WO2007012590A1 (fr) Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
DE60035247T2 (de) Gasturbinenschaufel
EP2282014A1 (fr) Section de canal d'écoulement annulaire pour une turbomachine
EP1675702B1 (fr) Turbine à gaz et aube mobile de turbomachine
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
EP2394028B1 (fr) Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale et son utilisation
EP1857635A1 (fr) Aube de turbine pour une turbine à gaz
EP2299056A1 (fr) Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube
EP3039246B1 (fr) Aube de turbine
EP3274561B1 (fr) Aube de rotor pour une turbine à gaz, procédé de fabrication et procédé de post-production
EP3232001A1 (fr) Aube rotorique de turbine
WO2018010918A1 (fr) Aube de turbine dotée d'ailettes de refroidissement en forme de barres
EP3623576B1 (fr) Aube de turbine à gaz
EP2650475B1 (fr) Pale pour une turbomachine, agencement d'aubes ainsi que la turbomachine
EP0492207B1 (fr) Aube pour machines à écoulement
EP3333366A1 (fr) Aube de turbine avec refroidissement du bord d'attaque
EP3536913A1 (fr) Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure

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: 20060724

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 HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

AKX Designation fees paid

Designated state(s): CH DE ES GB IT LI

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE ES GB IT LI

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: EP

REF Corresponds to:

Ref document number: 502005003344

Country of ref document: DE

Date of ref document: 20080430

Kind code of ref document: P

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2303163

Country of ref document: ES

Kind code of ref document: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20081222

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCAR

Free format text: SIEMENS SCHWEIZ AG;INTELLECTUAL PROPERTY FREILAGERSTRASSE 40;8047 ZUERICH (CH)

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

Ref country code: ES

Payment date: 20150928

Year of fee payment: 11

Ref country code: GB

Payment date: 20150812

Year of fee payment: 11

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

Ref country code: IT

Payment date: 20150825

Year of fee payment: 11

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

Ref country code: CH

Payment date: 20151102

Year of fee payment: 11

Ref country code: DE

Payment date: 20151016

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502005003344

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20160826

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: 20160831

Ref country code: CH

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

Effective date: 20160831

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: 20170301

Ref country code: GB

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

Effective date: 20160826

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 NON-PAYMENT OF DUE FEES

Effective date: 20160826

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 NON-PAYMENT OF DUE FEES

Effective date: 20160827

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20181128