EP1956190B1 - Profil pour une aube de turbine et installation de turbine - Google Patents

Profil pour une aube de turbine et installation de turbine Download PDF

Info

Publication number
EP1956190B1
EP1956190B1 EP07002546A EP07002546A EP1956190B1 EP 1956190 B1 EP1956190 B1 EP 1956190B1 EP 07002546 A EP07002546 A EP 07002546A EP 07002546 A EP07002546 A EP 07002546A EP 1956190 B1 EP1956190 B1 EP 1956190B1
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
curvature
blades
cross
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
EP07002546A
Other languages
German (de)
English (en)
Other versions
EP1956190A1 (fr
Inventor
Fathi Ahmad
Michael Kluck
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to DE502007001960T priority Critical patent/DE502007001960D1/de
Priority to EP07002546A priority patent/EP1956190B1/fr
Priority to AT07002546T priority patent/ATE448386T1/de
Publication of EP1956190A1 publication Critical patent/EP1956190A1/fr
Application granted granted Critical
Publication of EP1956190B1 publication Critical patent/EP1956190B1/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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • the present invention relates to an airfoil for a first stage blade of turbine turbine blades having a second stage of blades disposed behind the first stage of blades as viewed in an axial direction of the turbine plant.
  • a turbine plant has u. a. a gas or steam turbine with a working medium, d. H. Gas or steam, is operated.
  • the turbine may be coupled to a generator for power generation.
  • the turbine system usually includes a compressor for compressing air as a working medium.
  • the compressed air is supplied to a combustion chamber, where it is then combined with a fuel and burned.
  • the emerging from the combustion chamber hot working fluid is then fed to the turbine.
  • the compressor and the turbine usually include a rotatably mounted rotor on which a plurality of successively arranged rings of blades are attached.
  • the compressor and the turbine further include a stator to which a plurality of successively arranged rings of fixed vanes are attached.
  • the various rings of blades and vanes in the compressor and in the turbine are arranged alternately.
  • a ring of blades and a ring of vanes forms a stage of the turbine system.
  • Several stages form a shovel cascade.
  • FIG. 1 One of the blades that is commonly used in the turbine plant is exemplified in FIG. 1 shown.
  • a blade 1 has an airfoil 2, a blade root 3 and a platform 4.
  • the blade 1 is in FIG. 1 shown in a side view on a pressure side of the blade 1.
  • a reference character R denotes an axial direction of the turbine plant.
  • the blade 2 has a front edge 5, a trailing edge 6, a suction side facing side wall 7 (suction side wall) and a side facing the pressure side 8 (pressure side wall).
  • the pressure side wall 8 is shown in the illustration FIG. 1 seen in a plan view, while the suction side wall 7 rearward to the illustration after FIG. 1 is arranged.
  • FIG. 2 shows a representation of a cross-sectional area 9 of the airfoil 2 along a in FIG. 1 shown cross section II-II.
  • the airfoil 2 has in its interior a cavity 10 through which coolant for cooling the airfoil 2 can be passed. It is also possible to dispense with the cavity 6.
  • the airfoil 2 has a curvature or curvature 11 in the direction of the suction side.
  • the cross-sectional area 5 tapers continuously starting from the front edge 5 for the entry of the working medium to the trailing edge 6 for the discharge of the working medium.
  • the shape of the cross-sectional area 9 is relevant to the course of the flow of the working medium.
  • the present invention has for its object to enable a high efficiency in the operation of a turbine plant.
  • the airfoil of the turbine plant has a cross-sectional area which is designed in an S-shape.
  • the turbine system according to the invention contains the blade according to the invention.
  • the s-shaped cross-sectional area of the blade according to the invention advantageously ensures that an entry or incident angle of a flow of the working medium to a leading edge of a blade of a subsequent downstream flow of blades of the turbine plant can be adjusted very precisely and optimally in order to limit losses.
  • the present invention is based in particular on the recognition that this entry angle is partly responsible for the occurrence of eddy currents.
  • the inlet angle is also dependent on a temperature and a speed of the working medium, a further geometry of the turbine system, in particular the blade stages of the blade cascade, and a mass flow rate of the working medium.
  • the cross-sectional area of the blade according to the invention is advantageously designed such that it has a first curvature and, viewed in the axial direction, Having formed behind the first curvature second curvature, which is at least approximately opposite to the first curvature.
  • the first curvature is advantageously formed in the direction of the suction side and the second curvature in the direction of the pressure side.
  • the cross-sectional area thus has two arc-shaped curvatures which are formed in mutually at least approximately opposite directions and are arranged substantially one behind the other in the axial direction of the turbine installation.
  • the second camber or rear curve is formed in a region of the trailing edge of the airfoil.
  • the lower portion of the airfoil extends from the transition of the airfoil to the blade root of the airfoil in the radial direction to a height of the airfoil that corresponds to 10-15% of the total height of the airfoil. It could be advantageously determined that just in these 10-15% of the total height of the blade eddy currents occur that affect the efficiency of the turbine system particularly. These eddy currents can arise, for example, due to friction of the working medium on a platform of the blade. By the s-shaped configuration of the cross-sectional area of the blade in this lower region, the eddy currents can be reduced particularly suitable.
  • the s-shaped cross-sectional area is formed only in the lower portion of the airfoil. This is advantageously sufficient to severely limit the occurrence of the eddy currents.
  • the cross-sectional area of the remainder of the airfoil may then be advantageously adapted to other requirements. In particular, it is possible to limit the material and manufacturing costs.
  • the cross-sectional area viewed in a direction from a blade root to a blade head of the blade, designed s-shaped.
  • the entry angle can be set very precisely to avoid or reduce pressure losses.
  • an extent of the first curvature of the S-shaped cross-sectional area is greater than an extension of the second curvature of the S-shaped cross-sectional area. This ensures an even higher efficiency of the turbine system.
  • a radius of curvature of the first curvature or front curvature is thus greater than a curvature radius of the second curvature or rear curvature.
  • the s-shaped cross-sectional area is formed in a radially lower portion of the airfoil which is adjacent to a transition of the airfoil to the blade root of the airfoil. In this lower area occurring eddy currents can be particularly effectively prevented.
  • the airfoil is an airfoil of a blade of the turbine plant. Exactly between two adjacent blades of a ring of the turbine plant occur pronounced eddy currents, which can be significantly limited due to the inventive design of the airfoil.
  • FIG. 3 shows a representation of a section of a ring 12 of blades of a turbine of a turbine plant.
  • the present invention can also be used with blades of a compressor of the turbine system.
  • Blade feet of the blades are attached to a wheel disc and arranged over this on a rotor 13 of the turbine system.
  • the rotor 13 is rotatably mounted in the direction of rotation D about an axis of rotation pointing in the plane of the sheet.
  • the axis of rotation runs counter to an axial direction R of the turbine system.
  • Shown are a radially outwardly extending airfoil 14 of a blade 15 and a radially outwardly extending airfoil 16 of a blade 17.
  • the blades 15 and 17 are disposed adjacent and spaced apart along the circumference of a rotor 13.
  • the FIG. 3 schematically shows the cut rotor 13 and the blades 14, 16 from their trailing edges in the direction of their leading edges.
  • a lower eddy current 18 and an upper eddy current 19 are shown.
  • the lower eddy current 18 and the upper eddy current 19 run in the form of closed loops, in particular in the region of the trailing edges of the blades 14 and 16 between a suction side 20 of the blade 14 and a pressure side 21 of the blade 16.
  • the lower eddy current 18, viewed in the radial direction starting from a boundary region to the wheel disc or a transition to the blade roots up to such a height of the blades 14, 16, which in about 10-15% of Total height of the blades 14, 16 corresponds.
  • the upper eddy current 19 substantially, as viewed in the radial direction, adjoins the lower eddy current 18 and occurs from approximately 10-15% of the total height of the blades 14, 16 up to blade heads of the blades 15, 17.
  • the lower eddy current 18 at least partially generates the upper eddy current 19. This in turn is partly responsible for pressure losses that occur due to small gaps between the blade heads of the blades 15, 17 and a stator adjacent thereto.
  • the upper eddy flow 19 is also relevant to an inlet angle at which the flow of the working medium impinges on blades of a ring of blades of a downstream in the flow direction of the working medium or in the axial direction R stage. The entrance angle, unless properly set and adjusted, may be a cause of turbine efficiency losses.
  • FIG. 4 shows a side view of a pressure-side side wall 22 of a blade 23 of a blade 24 with exemplary and schematically illustrated vortex 25 of eddy currents of the working medium.
  • an effective height 26 of the airfoil 23 that is effectively available for performing work is determined.
  • This effective height 26 is smaller compared to the actual height of the airfoil 23.
  • the area of the side wall 22 defined by the effective height and width of the airfoil 23 is thus smaller than the area of the side wall 22 defined by the actual height and width of the airfoil 23.
  • FIG. 5 shows a representation of an S-shaped cross-sectional area 27 of a blade according to the invention 28 of a blade 29.
  • the blade 28 has the cross-sectional area 27 in the present embodiment exclusively in a lower portion of its radial expansion, starting from a transition to a platform or a blade root of the blade 29 to such a height, in the radial direction in about 10th -15% of the total height of the airfoil 28 corresponds.
  • the blade leaf 28 otherwise corresponds to the design of its cross-sectional area 27 in the lower area mentioned, the blade 2 according to the FIG. 1 ,
  • the airfoil 28 has in this respect the cross-sectional area 27 in the in FIG. 1 shown cross-section AA, which falls in the lower region.
  • the airfoil 28 has in this respect analogous to the representation of the airfoil 2 after FIG. 1 the front edge 5, the trailing edge 6, the suction side 20 facing side wall 7 (suction side wall) and the pressure side 21 facing side wall 8 (pressure side wall) on.
  • the cross-sectional area 27 has in the illustration after FIG. 5 , which shows a view in reverse radial direction from the blade head of the blade 29 in the direction of the platform, a shape of a "mirrored s". This accordingly means that the airfoil 28 has an s-shape in a view in the radial direction from the platform and the blade root of the blade 29 in the direction of the blade head.
  • the cross-sectional area 27 has, starting from the front edge 5 up to a region shortly before the trailing edge 6, a first curvature or first curvature 30 in the direction of the suction side 20. This first curvature 30 can largely correspond to the curvature 11 of the cross-sectional area 9 of the airfoil 2.
  • the extent of the curvature 30 in the longitudinal direction of the airfoil 28 can be made slightly shorter than the extension of the curvature 11 in the longitudinal direction of the airfoil 2.
  • the cross-sectional surface 27 tapers in the course of the first curvature 30 continuously starting from the front edge 5 to the area short in front of the trailing edge 6.
  • the cross-sectional area 27 has a second curvature or second curvature 31 in the direction of the pressure side 21.
  • the direction of the first curvature 30 is thus almost opposite to the direction of the second curvature 31.
  • the side wall 7 of the airfoil 28 has a convex wall surface, which is arched outwards towards the suction side 20.
  • the side wall 8 of the airfoil 28 has in this region of the first bulge 30 has a concave wall surface which is curved inwards.
  • the side wall 7 of the airfoil 28 in the region of the second curvature 31 has a concave wall surface, which is curved inwards.
  • the side wall 8 of the airfoil 28 has in this region of the second curvature 31 has a convex wall surface which is curved outwardly.
  • the extent of the first curvature 30 in the longitudinal direction of the airfoil 28 is made larger than the extent of the second curvature 31 in the longitudinal direction of the airfoil 28.
  • the airfoil 28 has in its interior in the region of the first curvature 30, the cavity 10, which is substantially the cavity 10 of the airfoil 2 according to FIG. 1 and can be passed through the coolant for cooling the airfoil 28. In the area of the second curvature 31, no hollow space for cooling is formed here.
  • an inlet angle 32 is shown below which the flow of the working medium impinges on the leading edge 5 of the airfoil 28.
  • the entrance angle 32 is here an opposite the axial direction R fixed, acute angle.
  • the entry angle 32 is influenced inter alia by the s-shaped configuration of the cross-sectional areas of the rotor blades of the preceding stage in the axial direction R or in the flow direction of the working medium. This S-shaped configuration of the cross-sectional area, and thus the entry angle 32 defined by it, is effective in particular against the occurrence of the lower eddy current 18, this lower eddy current 18 also having a significant influence on the occurrence of the upper eddy current 19.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Lame (28) d'aube pour une aube (29) d'un premier étage d'aubes d'une installation à turbine,
    qui a un deuxième étage de turbine qui, considéré dans une direction (R) axiale de l'installation à turbine, est disposé derrière le premier étage de turbine,
    dans lequel la lame (28) d'aube a une surface (27) de section transversale en forme de s,
    caractérisée en ce que la surface (27) de section transversale en forme de s est formée exclusivement dans une partie, inférieure en direction radiale, de la lame (28) d'aube partie qui est voisine d'une transition de la lame (28) d'aube à l'emplanture de l'aube (29).
  2. Lame d'aube suivant la revendication 1,
    caractérisée en ce que
    la surface (27) de section transversale est, considérée dans une direction allant de l'emplanture d'aube à une tête de l'aube (29), en forme de s.
  3. Lame d'aube suivant la revendication 1 ou 2,
    caractérisée en ce que
    une étendue d'une première courbure de la surface (27) de section transversale en forme de s est plus grande qu'une étendue d'une deuxième courbure (31) de la surface (27) de section transversale en forme de s.
  4. Lame d'aube suivant la revendication 1, 2 ou 3,
    caractérisée en ce que
    la partie inférieure de la lame (28) d'aube s'étend en partant de la transition de la lame (28) d'aube à l'emplanture de l'aube (29) en direction radiale jusqu'à une hauteur de la lame (28) d'aube qui correspond à 10 à 15% de la hauteur totale de la lame (28) d'aube.
  5. Lame d'aube suivant l'une des revendications précédentes,
    caractérisé en ce que
    c'est une lame (28) d'une aube mobile de l'installation à turbine.
  6. Installation à turbine ayant une lame (28) d'aube suivant l'une des revendications précédentes.
EP07002546A 2007-02-06 2007-02-06 Profil pour une aube de turbine et installation de turbine Not-in-force EP1956190B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE502007001960T DE502007001960D1 (de) 2007-02-06 2007-02-06 Schaufelblatt für eine Schaufel einer Turbinenanlage und Turbinenanlage
EP07002546A EP1956190B1 (fr) 2007-02-06 2007-02-06 Profil pour une aube de turbine et installation de turbine
AT07002546T ATE448386T1 (de) 2007-02-06 2007-02-06 Schaufelblatt für eine schaufel einer turbinenanlage und turbinenanlage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07002546A EP1956190B1 (fr) 2007-02-06 2007-02-06 Profil pour une aube de turbine et installation de turbine

Publications (2)

Publication Number Publication Date
EP1956190A1 EP1956190A1 (fr) 2008-08-13
EP1956190B1 true EP1956190B1 (fr) 2009-11-11

Family

ID=38069211

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07002546A Not-in-force EP1956190B1 (fr) 2007-02-06 2007-02-06 Profil pour une aube de turbine et installation de turbine

Country Status (3)

Country Link
EP (1) EP1956190B1 (fr)
AT (1) ATE448386T1 (fr)
DE (1) DE502007001960D1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1374182A (fr) * 1963-11-14 1964-10-02 Escher Wyss Sa Couronne d'aubes pour turbomachines assurant la déviation du fluide en circulation,tout en l'accélérant
FR1473721A (fr) * 1965-04-01 1967-03-17 Brown Ailettes mobiles pour écoulement transsonique
US7195456B2 (en) * 2004-12-21 2007-03-27 United Technologies Corporation Turbine engine guide vane and arrays thereof

Also Published As

Publication number Publication date
ATE448386T1 (de) 2009-11-15
EP1956190A1 (fr) 2008-08-13
DE502007001960D1 (de) 2009-12-24

Similar Documents

Publication Publication Date Title
DE69936184T2 (de) Abzapfringraum bei den Schaufelspitzen eines Gasturbinentriebwerks
EP1953344B1 (fr) Aube de turbine
EP2304186B1 (fr) Turbomachine axiale à faibles pertes du jeu des extrémités d'aubes
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
EP2024606B1 (fr) Conduit d'écoulement annulaire pour une turbomachine pouvant être traversée par un courant principal dans le sens axial
EP0799973B1 (fr) Contour de paroi pour une turbomachine axiale
EP2927503B1 (fr) Compresseur de turbine à gaz, moteur d'avion et méthode de dimensionnement
EP3999716B1 (fr) Aube de rotor pour une turbomachine, module de turbine associé et utilisation des mêmes
EP3536974B1 (fr) Compresseur de turbine à gaz
EP1774179B1 (fr) Aube de compresseur
EP2669474A1 (fr) Canal de passage pour une turbomachine et turbomachine
EP2818724B1 (fr) Turbomachine et procédé
EP2218918A1 (fr) Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites
EP2226509A2 (fr) Turbomachine de travail dotée d'une arrivée de fluide
WO2011124214A2 (fr) Aube directrice d'une machine d'écoulement
EP1012445B2 (fr) Aube pour une turbomachine
EP2846000B1 (fr) Roue statorique d'une turbine à gaz
EP4077882B1 (fr) Aube pour une turbomachine
WO2005116404A1 (fr) Aube comportant une zone de transition
EP3159487B1 (fr) Stator d'une turbine à gaz ayant un guidage d'air de refroidissement amélioré
EP3495639B1 (fr) Module de compresseur pour une turbomachine réduisant la couche limite dans un carter intermédiaire de compresseur
EP1723339A1 (fr) Compresseur d'une turbine a gaz ainsi que turbine a gaz
EP2987967B1 (fr) Carter de compresseur pour une turbine à gaz
WO2011088819A2 (fr) Système de boîtier pour une turbomachine axiale
EP3274561B1 (fr) Aube de rotor pour une turbine à gaz, procédé de fabrication et procédé de post-production

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 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 RS

17P Request for examination filed

Effective date: 20090213

AKX Designation fees paid

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

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

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 502007001960

Country of ref document: DE

Date of ref document: 20091224

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

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
LTIE Lt: invalidation of european patent or patent extension

Effective date: 20091111

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

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: 20091111

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: 20100311

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: 20091111

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: 20100222

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: 20100311

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: 20091111

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

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: 20091111

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: 20091111

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: 20091111

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: 20091111

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091111

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: 20091111

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: 20100211

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: 20091111

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: 20091111

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20100228

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

Ref country code: SK

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

Effective date: 20091111

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: 20091111

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

Ref country code: DE

Payment date: 20100419

Year of fee payment: 4

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: 20100812

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: 20100212

Ref country code: MC

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

Effective date: 20100301

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20101029

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: 20100301

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: 20100228

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

Ref country code: IT

Payment date: 20110223

Year of fee payment: 5

PGRI Patent reinstated in contracting state [announced from national office to epo]

Ref country code: IT

Effective date: 20110501

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

Ref country code: GB

Payment date: 20110210

Year of fee payment: 5

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: LI

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

Effective date: 20110228

Ref country code: CH

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

Effective date: 20110228

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502007001960

Country of ref document: DE

Effective date: 20110901

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

Ref country code: NL

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

Effective date: 20091111

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

Effective date: 20100512

Ref country code: LU

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

Effective date: 20100206

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

Effective date: 20120206

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: 20091111

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: 20120206

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: 20120206

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 448386

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120206

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: 20110901

Ref country code: AT

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

Effective date: 20120206