EP2352909B1 - Support d'aubes directrices - Google Patents

Support d'aubes directrices Download PDF

Info

Publication number
EP2352909B1
EP2352909B1 EP09783073.1A EP09783073A EP2352909B1 EP 2352909 B1 EP2352909 B1 EP 2352909B1 EP 09783073 A EP09783073 A EP 09783073A EP 2352909 B1 EP2352909 B1 EP 2352909B1
Authority
EP
European Patent Office
Prior art keywords
axial segments
turbine
support tube
axial
segments
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
EP09783073.1A
Other languages
German (de)
English (en)
Other versions
EP2352909A1 (fr
Inventor
Roderich Bryk
Oliver Strohmeier
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 EP09783073.1A priority Critical patent/EP2352909B1/fr
Publication of EP2352909A1 publication Critical patent/EP2352909A1/fr
Application granted granted Critical
Publication of EP2352909B1 publication Critical patent/EP2352909B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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
    • F05D2250/40—Movement of components
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/32—Articulated members
    • Y10T403/32008—Plural distinct articulation axes
    • Y10T403/32041—Universal
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/45—Flexibly connected rigid members
    • Y10T403/451—Rigid sleeve encompasses flexible bushing

Definitions

  • the invention relates to a guide vane carrier, in particular for a gas or steam turbine, which consists of a number of axial segments.
  • Gas or steam turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel or superheated steam is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, wherein compressed air is supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • For guiding the flow of the working medium in the turbine unit also commonly associated between adjacent blade rows with the turbine housing and combined into rows of guide vanes are arranged.
  • the vanes are fixed in each case via a blade root, also referred to as a platform, on a guide vane carrier of the turbine or compressor unit.
  • the guide vanes of the gas turbine can either be mounted on a common guide vane carrier be attached or separate axial segments are provided for each turbine or compressor stage, which are usually rigidly connected together.
  • the use of a plurality of axial segments offers the advantage that on the one hand smaller and therefore less expensive castings are used, on the other hand, the materials of the individual segments can be individually adapted to the physical boundary conditions prevailing in the respective axial region.
  • the vane carrier In stationary gas turbines, the vane carrier is still usually conical or cylindrical in shape and the vane carrier or its individual axial segments each consist of an upper and a lower segment, the z. B. are interconnected via flanges. Axially adjacent axial segments can in this case via a tie rod connection according to DE 190 159 be connected to each other.
  • the invention is therefore based on the object to provide a guide vane, which achieves a longer service life with a particularly high operational safety.
  • the invention is based on the consideration that a longer service life of the guide vane carrier would be achievable by avoiding too great a mechanical load due to a different deformation due to temperature differences.
  • a particularly high mechanical load occurs at Leitschaufelanin consisting of a plurality of axial segments, in particular in the connection region between the individual axial segments. Since this can lead to damage in a rigid connection of two axial segments, the connection should be flexible.
  • a flexible connection can be achieved, in particular, by the fact that the axial segments are not connected in a materially bonded manner, but are merely braced with one another in a form-fitting manner. For bracing the axial segments a number of tie rods is provided.
  • the tie rods can connect two adjacent axial segments in different ways, for example, by each coaxial openings are introduced into the respective axial segments, through which the tie rod is guided. Then, for example, nuts are set to a thread of the tie rod, which nut a larger diameter at the side facing away from the respective adjacent axial segment of the respective opening as the respective opening. As a result, the two axial segments are braced together without entering into a cohesive connection.
  • the aim of the arrangement of tie rods between the axial segments of the vane support is a compound that can absorb radial or axial displacements by their flexibility, without material damage caused by tensile or shear forces.
  • a greater flexibility can be achieved by a support tube is braced between the adjacent axial segments, which surrounds the respective tie rods.
  • Such a support tube serves as a spacer between the axial segments or the fixing points of the tie rod, which need not necessarily be arranged on each axial edge of the Axialsegments Axialsegments. Due to the greater distance between two axial segments, the flexibility of the connection is increased and damage due to mechanical stress is even better avoided. In this respect, the displacements of the axial segments against each other are made possible by the support tubes and tie rods.
  • a spherical disc is arranged at one end of the respective support tube, which is mounted in a cone cone arranged on the respective axial segment.
  • Spherical disc and conical socket then form a ball joint, which, however, has an opening for the continuous tie rod.
  • respective tie rods and the respective support tube are designed cylindrical and the inner diameter of the respective support tube is larger than the outer diameter of the respective tie rod.
  • This increases the flexibility of the connection in a torsion or shear of the axial segments against each other, since the support tube on the side facing the other axial segment rests while the tie rod is fixed by, for example, a nut on the opposite side.
  • This results in different fixed points in a caused by torsion movement of tie rods or support tube from the normal of the radial surface.
  • By a larger inner diameter of the support tube support tube and tie rods are always spaced apart in all radial directions and thus can tilt freely despite different fixed points against the normal of the radial surface.
  • the number of tie rods is at least six.
  • three tie rods can then be provided for each segment of the respective axial segment, so that a secure three-point connection of the respective segments of the axial segments arises.
  • the respective adjacent axial segments are connected to a universal joint.
  • a universal joint By such universal joints an additional gimbal coupling of the respective axial segments is achieved via which a centering and simultaneous transmission of the guiding torque from one to the other carrier is possible, for. B., if only one fixation is provided. This achieves an even safer connection with high flexibility at the same time.
  • the advantages achieved by the invention are in particular that a secure and at the same time flexible coupling of the axial segments is achieved by the connection of the axial segments of a guide vane carrier with tie rods.
  • a secure and at the same time flexible coupling of the axial segments is achieved by the connection of the axial segments of a guide vane carrier with tie rods.
  • FIG. 1 shows in detail a portion of a vane carrier 1.
  • the vane support 1 is usually conical or cylindrical shaped and consists of two segments, an upper and a lower segment, the z. B. are interconnected via flanges.
  • the guide vane carrier 1 shown comprises two axial segments 2.
  • the axial segments 2 are connected to one another via connecting bridges 4. Although this ensures a secure and dimensionally stable connection, however, shows the previous Operating experience that act by the different thermal deformation of the axial segments 2 high tensile and shear forces on the connecting bridges 4, which can lead to material failure.
  • each elastic connection 6 is detailed in FIG FIG. 3 shown.
  • the central element is the cylindrically massive tie rod 8, which is fastened at its ends 12 to a respective axial segment 2.
  • a hollow cylindrical support tube 14 is arranged. This acts as a spacer between the axial segments 2.
  • the connection between the axial segments 2 is made via suitable fastening devices on the axial segments 2 having corresponding openings.
  • the support tube 14 is arranged on the side facing the other axial segment 2, then the tie rod 8 is guided through openings and support tube 14, which is then clamped on the opposite side, for example, with nuts.
  • a solid, but not cohesive connection is reached, which can deform flexibly under tensile and shear forces within certain limits.
  • spherical washers 16 are attached to the respective axial ends of the support tube. These are arranged in corresponding conical cups 18, which are each attached to an associated axial segment 2.
  • the spherical discs 16 and conical cups 18 have an opening for the tie rod 8 and ensure a stable Stop with simultaneous flexible mounting of the support tube 14 to the axial segments. 2
  • the twist is in FIG. 3 based on the illustrated extensions 20 of the axis of the spherical discs 16 against the axis of the tie rod 8 can be seen.
  • the angle 22 between the respective axes is variable, without causing structural damage to the connection. Due to the ball bearing, the elastic connection 6 is therefore particularly easy to deform in the case of radial offset as well as in case of twisting of the respective regions of the axial segments 2, without losing stability.
  • the spherical discs 16 and conical cups 18 are again in FIG. 4 shown. These may, for example, be designed according to DIN 6319 and be adapted in their geometric dimensions and their material to the respective requirements with respect to stability and flexibility of the elastic connection 6.
  • the gas turbine 101 includes a compressor 102 for combustion air, a combustion chamber 104 and a turbine unit 106 for driving the compressor 102 and a generator, not shown, or a working machine.
  • the turbine unit 106 and the compressor 102 are arranged on a common turbine shaft 108, also referred to as a turbine runner, to which the generator or the working machine is also connected and which is rotatably mounted about its central axis 109.
  • the combustor 104 which is in the form of an annular combustor, is equipped with a number of burners 110 for combustion of a liquid or gaseous fuel.
  • the turbine unit 106 has a number of rotatable blades 112 connected to the turbine shaft 108.
  • the blades 112 are annularly disposed on the turbine shaft 108 and thus form a number of blade rows. Furthermore, the turbine unit 106 includes a number of stationary vanes 114, which are also attached in a donut-like manner to a vane support 1 of the turbine unit 106 to form rows of vanes.
  • the blades 112 serve to drive the turbine shaft 108 by momentum transfer from the turbine unit 106 flowing through the working medium M.
  • the vanes 114 serve to flow the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 114 or a row of vanes and a ring of blades 112 or a blade row is also referred to as a turbine stage.
  • Each vane 114 has a platform 118 which is arranged to fix the respective vane 114 to a vane support 1 of the turbine unit 106 as a wall element.
  • the platform 118 is a thermally comparatively heavily loaded component, which forms the outer boundary of a hot gas channel for the turbine unit 106 flowing through the working medium M.
  • Each blade 112 is fastened to the turbine shaft 108 in an analogous manner via a platform 119, also referred to as a blade root.
  • a guide ring 121 is arranged on a guide blade carrier 1 of the turbine unit 106.
  • the outer surface of each guide ring 121 is also exposed to the hot, the turbine unit 106 flowing through the working medium M and spaced in the radial direction from the outer end of the blades opposite him 112 through a gap.
  • the guide rings 121 arranged between adjacent rows of guide blades serve in particular as cover elements which support the inner housing in the guide blade carrier 1 or protect other housing-mounted components from thermal overload by the hot working medium M flowing through the turbine 106.
  • the combustion chamber 104 is configured in the exemplary embodiment as a so-called annular combustion chamber, in which a plurality of burners 110 arranged around the turbine shaft 108 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 104 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 108 around.
  • a guide vane carrier 1 of the above-mentioned embodiment By the use of a guide vane carrier 1 of the above-mentioned embodiment, an increased service life and lower repair susceptibility of the gas turbine 1 is achieved. Damage to the vane support 1 due to thermal deformation of the axial segments 2 is avoided by the elastic connections 6.
  • the guide blade carrier 1 can also be used in the compressor 102 or in a steam turbine.

Landscapes

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

Claims (6)

  1. Support ( 1 ) d'aubes directrices,
    notamment pour une turbine ( 101 ) à gaz ou à vapeur,
    qui a un certain nombre de segments ( 2 ) axiaux,
    dans lequel deux segments ( 2 ) axiaux directement voisins sont reliés par un certain nombre de tirants ( 8 ) entourés respectivement d'un tuyau ( 4 ) d'appui, caractérisé en ce que
    à au moins une extrémité, de préférence aux deux extrémités du tuyau ( 14 ) d'appui respectif, est disposée une rondelle ( 16 ) à portée sphérique, qui est montée dans une crapaudine ( 18 ) conique s'appuyant sur le segment ( 2 ) axial respectif.
  2. Support ( 1 ) d'aubes directrices suivant la revendication 1,
    dans lequel le tirant ( 8 ) respectif et le tuyau ( 14 ) d'appui respectif sont conçus cylindriquement et le diamètre intérieur du tuyau ( 14 ) d'appui respectif est plus grand que le diamètre extérieur du tirant ( 8 ) respectif.
  3. Support ( 1 ) d'aubes directrices suivant la revendication 1 ou 3,
    dans lequel le nombre des tirants ( 8 ) est d'au moins six.
  4. Support ( 1 ) d'aubes directrices suivant la revendication 1, 2 ou 3,
    dans lequel les segments ( 2 ) axiaux voisins respectifs sont reliés par une articulation à la cardan.
  5. Turbine ( 101 ) à gaz ou à vapeur ayant un support ( 1 ) d'aubes directrices suivant l'une des revendications 1 à 4.
  6. Installation de turbine à gaz et de turbine à vapeur ayant une turbine ( 101 ) à gaz et/ou à vapeur suivant la revendication 5.
EP09783073.1A 2008-12-03 2009-09-16 Support d'aubes directrices Not-in-force EP2352909B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09783073.1A EP2352909B1 (fr) 2008-12-03 2009-09-16 Support d'aubes directrices

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08020992A EP2194239A1 (fr) 2008-12-03 2008-12-03 Support d'aubes directrices
EP09783073.1A EP2352909B1 (fr) 2008-12-03 2009-09-16 Support d'aubes directrices
PCT/EP2009/061996 WO2010063500A1 (fr) 2008-12-03 2009-09-16 Support d'aube directrice

Publications (2)

Publication Number Publication Date
EP2352909A1 EP2352909A1 (fr) 2011-08-10
EP2352909B1 true EP2352909B1 (fr) 2016-01-13

Family

ID=40823290

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08020992A Withdrawn EP2194239A1 (fr) 2008-12-03 2008-12-03 Support d'aubes directrices
EP09783073.1A Not-in-force EP2352909B1 (fr) 2008-12-03 2009-09-16 Support d'aubes directrices

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08020992A Withdrawn EP2194239A1 (fr) 2008-12-03 2008-12-03 Support d'aubes directrices

Country Status (4)

Country Link
US (1) US8672616B2 (fr)
EP (2) EP2194239A1 (fr)
CN (1) CN102245863A (fr)
WO (1) WO2010063500A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012222449A1 (de) * 2012-12-06 2014-06-26 Siemens Aktiengesellschaft Dynamoelektrische Maschine mit segmentiertem Aufbau des Stators und/oder Rotors

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE190159C (fr) * 1907-10-25
GB589541A (en) * 1941-09-22 1947-06-24 Hayne Constant Improvements in axial flow turbines, compressors and the like
FR1057993A (fr) * 1952-04-08 1954-03-12 Rolls Royce Perfectionnements aux turbo-machines
US2934316A (en) * 1955-11-18 1960-04-26 Worthington Corp Turbine casing
US3625550A (en) * 1969-10-31 1971-12-07 Edouard Beyeler Union joint for tubing
US4684320A (en) * 1984-12-13 1987-08-04 United Technologies Corporation Axial flow compressor case
US4840410A (en) * 1988-05-05 1989-06-20 Welkey Joseph J Apparatus for making a swiveled flow line connection
JPH11343807A (ja) * 1998-06-01 1999-12-14 Mitsubishi Heavy Ind Ltd 蒸気タービンの連結静翼
US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface

Also Published As

Publication number Publication date
CN102245863A (zh) 2011-11-16
EP2352909A1 (fr) 2011-08-10
EP2194239A1 (fr) 2010-06-09
US8672616B2 (en) 2014-03-18
US20110236213A1 (en) 2011-09-29
WO2010063500A1 (fr) 2010-06-10

Similar Documents

Publication Publication Date Title
EP2342427B1 (fr) Support d'aubes statorique axialement segmenté d'une turbine à gaz
EP2617979B1 (fr) Dispositif de dégivrage pour turbine à gaz
EP2527253B1 (fr) Dispositif de dégivrage d'une turbine à gaz volatil
DE102007031712A1 (de) Vorrichtung und Verfahren zum Einspannen von beschaufelten Rotorscheiben eines Strahltriebwerkes
EP2342425B1 (fr) Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
EP2344723B1 (fr) Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
EP2211023A1 (fr) Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
EP1970532A1 (fr) Rotor d'une turbomachine thermique tout comme turbine à gaz
DE102015116935A1 (de) Sicherungsvorrichtung zur axialen Sicherung einer Laufschaufel und Rotorvorrichtung mit einer derartigen Sicherungsvorrichtung
EP2025867A1 (fr) Rotor pour une turbomachine
EP3176386B1 (fr) Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
EP2347101B1 (fr) Turbine à gaz et moteur à turbine à gaz associé
EP2206885A1 (fr) Turbine à gaz
EP2352909B1 (fr) Support d'aubes directrices
EP1731715A1 (fr) Transition d'une chambre de combustion à une turbine
EP2526263A2 (fr) Système de boîtier pour une turbomachine axiale
EP2347100B1 (fr) Turbine à gaz avec insert de refroidissement
EP1429077B1 (fr) Turbine à gaz
EP2218882A1 (fr) Système de support d'aube directrice
WO2004031656A1 (fr) Turbine a gaz
EP1564376B1 (fr) Construction de rotor pour turbomachine
DE919802C (de) Einrichtung zur Befestigung von Laufschaufeln fuer axial durchstroemte Kreiselradmaschinen
EP3492712B1 (fr) Dispositif support pour un boîtier d'une turbomachine, boîtier pour une turbomachine et turbomachine
EP0799971B1 (fr) Barrière thermique pour rotor de turbine
DE10233881B4 (de) Durch thermische Effekte radial veränderbares Ringelement

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: 20110513

AK Designated contracting states

Kind code of ref document: A1

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

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150803

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 HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

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: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 770663

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160215

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009012054

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: 20160113

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: 20160113

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: 20160113

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: 20160113

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: 20160113

Ref country code: NO

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

Effective date: 20160413

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: 20160414

Ref country code: HR

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

Effective date: 20160113

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: 20160113

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: 20160113

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: 20160513

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: 20160113

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: 20160113

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: 20160513

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009012054

Country of ref document: DE

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

Ref country code: EE

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

Effective date: 20160113

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: 20160113

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: 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: 20160113

Ref country code: SM

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

Effective date: 20160113

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: 20160113

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: 20160113

26N No opposition filed

Effective date: 20161014

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: 20160930

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: 20160113

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: 20160413

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009012054

Country of ref document: DE

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

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: 20160113

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: 20160916

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: 20170531

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

Ref country code: CH

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

Effective date: 20160930

Ref country code: FR

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

Effective date: 20160930

Ref country code: IE

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

Effective date: 20160916

Ref country code: GB

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

Effective date: 20160916

Ref country code: DE

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

Effective date: 20170401

Ref country code: LI

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

Effective date: 20160930

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: 20160916

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 770663

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160916

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20160930

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: 20160916

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: 20160113

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: 20090916

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

Ref country code: MK

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

Effective date: 20160113

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: 20160113

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: 20160113