EP2087207B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

Info

Publication number
EP2087207B1
EP2087207B1 EP07821492.1A EP07821492A EP2087207B1 EP 2087207 B1 EP2087207 B1 EP 2087207B1 EP 07821492 A EP07821492 A EP 07821492A EP 2087207 B1 EP2087207 B1 EP 2087207B1
Authority
EP
European Patent Office
Prior art keywords
cooling
ribs
rib
turbine blade
pair
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
EP07821492.1A
Other languages
German (de)
English (en)
Other versions
EP2087207A1 (fr
Inventor
Heinz-Jürgen GROSS
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 EP07821492.1A priority Critical patent/EP2087207B1/fr
Publication of EP2087207A1 publication Critical patent/EP2087207A1/fr
Application granted granted Critical
Publication of EP2087207B1 publication Critical patent/EP2087207B1/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
    • F01D5/187—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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • 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
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a turbine blade.
  • Turbine blades particularly turbine blades for gas turbines, are exposed during operation to high temperatures which rapidly exceed the limit of material stress. This applies in particular to the areas in the vicinity of the flow inlet edge.
  • it has long been known to cool turbine blades suitable, so that they have a higher temperature resistance. With turbine blades, which have a higher temperature resistance, higher energy efficiencies can be achieved in particular.
  • Cooling cooling is probably the most common type of blade cooling.
  • This type of cooling cooling air is passed through channels in the interior of the blade and uses the convective effect to dissipate the heat.
  • impingement cooling a cooling air flow impinges on the blade surface from the inside. In this way, a very good cooling effect is made possible at the point of impact, but this is limited only to the narrow area of the point of impact and the closer environment.
  • This type of cooling is therefore usually used for cooling the flow inlet edge of a turbine blade, which is exposed to high temperature loads.
  • film cooling cooling air is directed outward through openings in the turbine blade from inside the turbine blade. This cooling air flows around the turbine blade and forms an insulating layer between the hot process gas and the blade surface.
  • the types of cooling described are suitably combined depending on the application in order to achieve the most effective blade cooling possible.
  • coolants such as turbulators, which are usually provided in the form of low ribs, very common and for example from the EP 1 637 699 A2 known.
  • the fins are disposed within the convection flow provided cooling channels that run inside the turbine blade.
  • the incorporation of fins in the cooling channels causes the flow of cooling air in the boundary layers to be detached and entangled. Due to the forced disruption of the flow, the heat transfer can be increased in the presence of a temperature difference between the cooling channel wall and the cooling air.
  • the ribbing constantly causes the flow to form new "recovery areas" in which a substantial increase in the local heat transfer coefficient can be achieved.
  • cooling channels are often formed in turbine blades parallel to and close to the flow inlet edge, to which cooling air is supplied by further cooling channels formed in the blades.
  • the convective cooling of the flow inlet edge realized in this way is usually supplemented in the case of film-cooled blades by an impingement cooling of the inner wall of the cooling channel running close to the flow inlet edge.
  • convective cooling is intensified by turbulators disposed on the inner wall of the cooling duct.
  • the invention has for its object to provide a turbine blade whose flow inlet edge can be cooled more effectively compared to known solutions, both in existing as well as non-existing film cooling.
  • a turbine blade which has a plurality of ribs, which are arranged successively in a cooling channel which extends along a flow inlet edge, and in which each with two ribs a pair of ribs is formed, arranged the ribs in skating step shape are.
  • the inventively provided pairwise arrangement of the ribs in skate step shape causes over known solutions a greatly increased turbulence of the cooling air flowing in the cooling channel according to the invention, such that the cooling air flowing in the cooling channel from one rib of a rib-pair on the other rib of the ribs Pair is headed.
  • a greatly increased turbulence of the cooling air a greatly increased local heat transfer coefficient is connected, so that overall, compared to known solutions, a significantly more effective cooling, in particular in the region of the flow inlet edge, can be provided.
  • the turbine blade according to the invention can thus be exposed to higher gas temperatures, even if no film cooling is provided. If film cooling is provided, even higher gas temperatures are possible.
  • a high degree of turbulence is formed on the flowed-on ribs, which, in combination with impingement cooling effects and a strong increase in surface area on the cooling air side, leads to efficient use of cooling air and equalization of the temperature distribution.
  • the two ribs of a rib-pair are each formed as a guide element for a core flow of a cooling medium flowing in the cooling channel, such that the ribs direct the core flow of a rib of the rib-pair substantially transversely to the other rib of the rib-pair ,
  • a particularly large proportion namely the cooling medium stream flowing in the center of the channel, is guided as an impact cooling jet against the side surfaces of the downstream ribs, so that in the region of the ribbed pair a very high local heat transfer coefficient and a According strong trained cooling effect can be achieved.
  • a core flow of the medium flowing in the cooling channel is understood to mean that part of the cooling medium that flows essentially in the center of the channel, ie, that does not flow essentially along the channel walls.
  • the ribs according to the invention are not turbulators in the sense of EP 1 637 699 A2 but guide elements with which a significant proportion of the cooling medium can be deflected or diverted each.
  • the two ribs of a rib pair include a predetermined angle, and a total cooling capacity of the two ribs of a rib pair is adjusted over the angle to a predetermined cooling requirement for the flow inlet edge in the vicinity of the rib pair.
  • the extent of the turbulence of the cooling air and thus also the local heat transfer coefficient can be selectively influenced, so that cooling adapted to a local cooling requirement for the flow inlet edge can be realized.
  • the cooling ability of a pair of ribs by increasing the angle of the two ribs of the rib-pair is included, be enlarged.
  • the temperature distribution at the flow inlet edge can be "made uniform" by means of this practical development, since according to the invention comparatively hot spots of the flow inlet edge by appropriately trained rib pairs a correspondingly strong cooling and vice versa, so that an effective cooling of the flow inlet edge can be realized which counteracts an inhomogeneous temperature distribution.
  • An inhomogeneous temperature distribution is associated with high thermal loads, which adversely affect the life of the turbine. This applies in particular to turbine blades which are used in axially through-flow turbines in which an inhomogeneous temperature distribution along the radial direction is formed for the flow inlet edge.
  • the ribs extend projecting from a wall bounding the cooling channel into the cooling channel, the ribs preferably being formed integrally with the bounding wall.
  • the rib pairs are mounted within an insert which is inserted into the cooling channel.
  • an insert is provided according to the invention, which can optionally be removed from the turbine blade, preferably in the form of a guide vane, to adapt, for example, the angular position of the rib pairs of a given application.
  • the casting of the turbine blade can thus be kept simple so that the turbine blade according to the invention can also be produced without elaborately designed casting cores.
  • the cooling channel extends parallel to the flow inlet edge continuously through the Turbine blade to provide effective cooling along the entire extent of the flow entry edge.
  • FIG. 1 shows a sketch-like sectional view of a turbine blade 10 according to the invention by the flow inlet edge 12.
  • the section according to the sectional area AA of FIG. 1 is in FIG. 3 this is a sketch-like sectional view of the front portion of a turbine blade 10 according to the invention.
  • a cooling channel 14 extending parallel to the flow inlet edge 12 is formed near the flow inlet edge 12 (ie a radially extending channel 14 in the case of axially through-flowed turbines).
  • the cooling channel 14 are in this successively a number of rib pairs 24 (in FIG. 1 hidden), wherein the individual ribs 18 of each pair of ribs 24 are set transversely to each other by a predetermined angle ⁇ .
  • the ribs 18 of a pair of ribs 24, viewed along the cooling channel extension, are arranged offset to one another.
  • the ribs 18 of each pair 24 and the ribs 18 of immediately adjacent pairs 24 are thus arranged overlapping in skating step shape.
  • the ribs 18 according to the invention are designed as guide elements for the cooling air flowing in the center of the cooling channel 14 in order to mutually guide the substantial portion of the cooling air flowing there to the side surfaces of the following ribs 18. Accordingly, the ribs 18 according to the invention protrude considerably further into the cooling channel 18 than the turbulators of FIG EP 1 637 699 A2 which are compared to the ribs 18 only to be near the surface and also do not conduct or deflect a significant proportion of the cooling air.
  • the cooling air When flowing through the cooling channel 14, the cooling air is alternately deflected by the individual ribs 18 of each pair 24. A high degree of turbulence is formed at the bulging ribs 18, which flows in a transverse direction, which, in combination with impingement cooling effects and the associated cooling air-side surface enlargement, leads to an efficient use of cooling air.
  • the angle ⁇ in the central region of the turbine blade 10 is greater than in the edge regions of the turbine blade 10, so as to cool the middle, during operation usually strongly heated area of the flow inlet edge 12 stronger than the edge regions of the flow inlet edge 12 by an enlargement of the angle ⁇ , the cooling air is deflected more strongly, with a concomitant increased turbulence, which ultimately has a more pronounced increase in the local heat transfer coefficient compared to smaller angles.
  • the inhomogeneous temperature distribution which forms along the flow inlet edge 12 when the turbine blade 10 is used can be counteracted.
  • Suitable values for the angle ⁇ , which are adapted to the respective cooling requirement, according to the invention are in the range of about 60 ° to 90 °.
  • FIG. 2 is the sketchy sectional view of the front portion of the turbine blade 10 according to the invention according to FIG. 1
  • the individual ribs 18 of a pair 24 extend predominantly from a front wall 16 of the cooling channel 14 to a rear wall 20 of the cooling channel 14.
  • the ribs 18 may also be part of an insert which can be inserted in the cooling channel 14.
  • the cooling air can preferably be guided in the direction of the front wall 16 by suitably setting the angular position ⁇ , in order to achieve the most effective possible cooling of the flow inlet edge 12.
  • provided angular sizes are in the range of about 30 ° to 60 °.

Landscapes

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

Claims (6)

  1. Aube (10) de turbine ayant plusieurs ailettes (8), qui se succèdent dans un conduit (14) de refroidissement s'étendant suivant un bord (12) d'entrée de l'écoulement, et dans laquelle il est formé par respectivement deux ailettes (18) une paire (24) d'ailettes, dont les ailettes (18) sont disposées sous la forme d'un pas de patin à glace, caractérisée
    en ce que les deux ailettes (18) d'une paire (24) d'ailettes sont respectivement sous la forme d'un élément de conduite d'un courant de coeur d'un fluide de refroidissement passant dans le conduit (14) de refroidissement, de manière à ce que les ailettes (18) conduisent le courant de coeur sensiblement transversalement d'une ailette (18) de la paire (24) d'ailettes à l'autre nervure (18) de la paire (24) d'ailettes.
  2. Aube (10) de turbine suivant la revendication 1,
    dans laquelle les deux ailettes (18) d'une paire (24) d'ailettes font un angle défini à l'avance et en ce qu'un pouvoir global de refroidissement des deux ailettes (18) d'une paire (24) d'ailettes est adapté par l'angle à un besoin de refroidissement donné à l'avance du bord (12) d'entrée d'écoulement à l'entour de la paire (24) d'ailettes.
  3. Aube (10) de turbine suivant la revendication 1 ou 2, dans laquelle les ailettes (18) s'étendent dans le conduit (14) de refroidissement en partant d'une paroi (16, 20) délimitant le conduit (14) de refroidissement.
  4. Aube (10) de turbine suivant la revendication 3,
    dans laquelle les ailettes (18) sont constituées d'une seule pièce avec la paroi (16, 20) de limitation.
  5. Aube (10) de turbine suivant l'une des revendications 1 à 3,
    dans laquelle les paires (24) d'ailettes sont mises à l'intérieur d'un insert qui est poussé dans le conduit (14) de refroidissement.
  6. Aube (10) de turbine suivant l'une des revendications précédentes,
    caractérisée en ce que le conduit (14) de refroidissement s'étend parallèlement au bord (12) d'entrée de l'écoulement de bout en bout dans l'aube (10) de turbine.
EP07821492.1A 2006-11-09 2007-10-18 Aube de turbine Not-in-force EP2087207B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07821492.1A EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06023377A EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine
EP07821492.1A EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine
PCT/EP2007/061127 WO2008055764A1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Publications (2)

Publication Number Publication Date
EP2087207A1 EP2087207A1 (fr) 2009-08-12
EP2087207B1 true EP2087207B1 (fr) 2016-04-20

Family

ID=37909821

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06023377A Withdrawn EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine
EP07821492.1A Not-in-force EP2087207B1 (fr) 2006-11-09 2007-10-18 Aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06023377A Withdrawn EP1921269A1 (fr) 2006-11-09 2006-11-09 Aube de turbine

Country Status (4)

Country Link
US (1) US8215909B2 (fr)
EP (2) EP1921269A1 (fr)
JP (1) JP5329418B2 (fr)
WO (1) WO2008055764A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120076660A1 (en) * 2010-09-28 2012-03-29 Spangler Brandon W Conduction pedestals for a gas turbine engine airfoil
US8920122B2 (en) 2012-03-12 2014-12-30 Siemens Energy, Inc. Turbine airfoil with an internal cooling system having vortex forming turbulators
WO2018153796A1 (fr) * 2017-02-24 2018-08-30 Siemens Aktiengesellschaft Pale ou aube de turbomachine ayant un canal de refroidissement avec un agencement croisé de broches
GB2574368A (en) * 2018-04-09 2019-12-11 Rolls Royce Plc Coolant channel with interlaced ribs
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
US10989067B2 (en) 2018-07-13 2021-04-27 Honeywell International Inc. Turbine vane with dust tolerant cooling system
US10669862B2 (en) 2018-07-13 2020-06-02 Honeywell International Inc. Airfoil with leading edge convective cooling system
GB201902997D0 (en) 2019-03-06 2019-04-17 Rolls Royce Plc Coolant channel
US11230929B2 (en) 2019-11-05 2022-01-25 Honeywell International Inc. Turbine component with dust tolerant cooling system

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
JP3006174B2 (ja) * 1991-07-04 2000-02-07 株式会社日立製作所 内部に冷却通路を有する部材
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5472316A (en) * 1994-09-19 1995-12-05 General Electric Company Enhanced cooling apparatus for gas turbine engine airfoils
DE19526917A1 (de) * 1995-07-22 1997-01-23 Fiebig Martin Prof Dr Ing Längswirbelerzeugende Rauhigkeitselemente
JP3396360B2 (ja) * 1996-01-12 2003-04-14 三菱重工業株式会社 ガスタービン冷却動翼
DE19634238A1 (de) * 1996-08-23 1998-02-26 Asea Brown Boveri Kühlbare Schaufel
US5797726A (en) * 1997-01-03 1998-08-25 General Electric Company Turbulator configuration for cooling passages or rotor blade in a gas turbine engine
DE59709195D1 (de) * 1997-07-14 2003-02-27 Alstom Switzerland Ltd Kühlsystem für den Vorderkantenbereich einer hohlen Gasturbinenschaufel
EP1191189A1 (fr) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Aube de turbine à gaz
US6742991B2 (en) * 2002-07-11 2004-06-01 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
US7094031B2 (en) * 2004-09-09 2006-08-22 General Electric Company Offset Coriolis turbulator blade
US8690538B2 (en) * 2006-06-22 2014-04-08 United Technologies Corporation Leading edge cooling using chevron trip strips
US20070297916A1 (en) * 2006-06-22 2007-12-27 United Technologies Corporation Leading edge cooling using wrapped staggered-chevron trip strips

Also Published As

Publication number Publication date
JP2010509535A (ja) 2010-03-25
EP2087207A1 (fr) 2009-08-12
US8215909B2 (en) 2012-07-10
WO2008055764A1 (fr) 2008-05-15
EP1921269A1 (fr) 2008-05-14
JP5329418B2 (ja) 2013-10-30
US20100054952A1 (en) 2010-03-04

Similar Documents

Publication Publication Date Title
EP2087207B1 (fr) Aube de turbine
EP2087206B1 (fr) Aube de turbine
EP1223308B1 (fr) Composante d'une turbomachine
EP1113145B1 (fr) Aube pour turbine a gaz avec section de mesure sur le bord de fuite
DE69838015T2 (de) Schaufelkühlung
DE602005000350T2 (de) Turbinenstatorschaufel mit verbesserter Kühlung
DE2320581C2 (de) Gasturbine mit luftgekühlten Turbinenlaufschaufeln
EP3658751B1 (fr) Aubage d'aube de turbine
EP0798448A2 (fr) Système et dispositif pour réfroidir une paroi chauffée d'un cÔté par un gaz chaud
DE102011000878B4 (de) Turbinenschaufel mit abgeschirmtem Kühlmittelzuführungskanal
DE60122050T2 (de) Turbinenleitschaufel mit Einsatz mit Bereichen zur Prallkühlung und Konvektionskühlung
WO2010003725A1 (fr) Aube de turbine pour une turbine à gaz et noyau de coulée pour sa fabrication
EP2126286A1 (fr) Aube de turbine
EP1292760B1 (fr) Configuration d'une aube de turbine pouvant etre refroidie
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
CH706962B1 (de) Serpentinenkühlung der Leitschaufelendwand.
EP1207269B1 (fr) Aube de turbine à gaz
DE112016001691B4 (de) Turbinenschaufel und Gasturbine
EP3087254B1 (fr) Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
EP0992653A1 (fr) Composants réfroidis par couche d'air avec perçages de refroidissement à section transversale triangulaire
EP1046784A1 (fr) Structure refroidie
DE19845147B4 (de) Vorrichtung und Verfahren zur Kühlung einer einseitug von Heißgas umgebenen Wand
EP2918780A1 (fr) Composant refroidi par impact pour une turbine à gaz
EP1998115A1 (fr) Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud
EP3587748B1 (fr) Structure de boîtier pour une turbomachine, turbomachine et procédé de refroidissement d'une section de boîtier d'une structure de boîtier d'une turbomachine

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: 20090409

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 MT NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20111118

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502007014750

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0005180000

Ipc: F01D0005140000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/14 20060101AFI20151021BHEP

Ipc: F01D 5/18 20060101ALI20151021BHEP

INTG Intention to grant announced

Effective date: 20151111

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 MT 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: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 792679

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502007014750

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160420

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: 20160420

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: 20160420

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: 20160420

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: 20160420

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

Ref country code: ES

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

Effective date: 20160420

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: 20160721

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: 20160420

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: 20160822

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: 20160420

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: 20160420

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502007014750

Country of ref document: DE

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

Ref country code: RO

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

Effective date: 20160420

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: 20160420

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: 20160420

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: 20160420

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: 20160420

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

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

Ref country code: BE

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

Effective date: 20161031

26N No opposition filed

Effective date: 20170123

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502007014750

Country of ref document: DE

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: 20160420

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: 20161018

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170630

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: 20161018

Ref country code: CH

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

Effective date: 20161031

Ref country code: LI

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

Effective date: 20161031

Ref country code: DE

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

Effective date: 20170503

Ref country code: FR

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

Effective date: 20161102

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: 20161018

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: 20161018

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20161031

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 792679

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161018

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

Ref country code: AT

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

Effective date: 20161018

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: 20160420

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: 20071018

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: 20160420

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: 20160420

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: 20160420

Ref country code: MT

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

Effective date: 20160420

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

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: 20160420