EP1079070A2 - Bouclier thermique pour un rotor de turbine - Google Patents

Bouclier thermique pour un rotor de turbine Download PDF

Info

Publication number
EP1079070A2
EP1079070A2 EP00810682A EP00810682A EP1079070A2 EP 1079070 A2 EP1079070 A2 EP 1079070A2 EP 00810682 A EP00810682 A EP 00810682A EP 00810682 A EP00810682 A EP 00810682A EP 1079070 A2 EP1079070 A2 EP 1079070A2
Authority
EP
European Patent Office
Prior art keywords
heat accumulation
accumulation unit
rotor
contour
rotor disks
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.)
Granted
Application number
EP00810682A
Other languages
German (de)
English (en)
Other versions
EP1079070B1 (fr
EP1079070A3 (fr
Inventor
Herbert Brandl
Peter Marx
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 Alstom Technology AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical Alstom Technology AG
Publication of EP1079070A2 publication Critical patent/EP1079070A2/fr
Publication of EP1079070A3 publication Critical patent/EP1079070A3/fr
Application granted granted Critical
Publication of EP1079070B1 publication Critical patent/EP1079070B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components

Definitions

  • the invention relates to a device for separating a hot Working area flowed through a preferably coolable, Space within a rotor arrangement of a turbomachine, preferably a gas turbine, with at least two axially one behind the other Rotor disks that can be firmly connected to one another via at least one connection area are and at least in the area of their radial peripheral edges from each other are spaced, and with a flat heat accumulation unit, which between two adjacent rotor disks are arranged and two connecting edges has, along which the heat accumulation unit in each case in the region of the peripheral edges the adjacent rotor disks can be brought into operative connection, and some Interspace extending between the two rotor disks on the rotor side covers.
  • the heat accumulation units mainly serve to shape the interior a gas turbine provided hot gas channel on its facing the rotor Diameter and protects rotor structure parts against overheating.
  • the heat accumulation units described above are part of axial turbomachines, flow through the gaseous working media for compression or targeted expansion and due to their high process temperatures, those with the hot working media subject the system components to direct thermal stress.
  • rotating rotor components To protect a high heat input are known in the field the blade feet or the peripheral edges of the rotor disks are annular Heat accumulation units are provided, which are used for sealing the rotor with the Rotation shaft connected rotor disks opposite the hot flow channel to care.
  • Figure 1 is a cross-sectional view through two adjacent rotor disks a screwed rotor shown, on the screw connection not in detail is received.
  • the neighboring ones rotating about an axis of rotation A.
  • Rotor disks 1, 2 see 3 receiving units on their peripheral peripheral edge for the connection of blades 4, 5 before. Here they open in the manner of a fir tree structure trained blade feet in corresponding counter contours in the rotor disks 1, 2.
  • a guide vane 12 is introduced between the two adjacent rotor blades 4, 5 in the case of a gas turbine stage.
  • Via screw connections 6, 7 is an annular between the two adjacent rotor disks 1, 2 Heat accumulation unit 8 firmly integrated.
  • the heat accumulation unit 8 forms a closed one Contour with the outer radii of the rotor disks 1, 2 and enables in this way the separation of a cooling air fed into the rotor into the intermediate space 9 of the hot runner 10 located radially above the heat accumulation unit one is the heat accumulation unit 8 for reasons of its sealing function with the lowest possible Form sealing points, on the other hand, the construction of the heat accumulation unit 8 taking into account those acting on them due to the rotation Train centrifugal forces.
  • FIG 2 shows the cross section through two rotor disks 1, 2 of a welded one Rotor arrangement shown.
  • Welded Disc rotors require access after their preliminary assembly to the welds 11 between the rotor disks 1, 2.
  • Da a closed ring-shaped heat accumulation unit 8 between the cavity 9 would close the rotor disks 1, 2, would be access to the Welded seams 11 of the rotor hindered.
  • the invention has for its object to provide a device for separating a a hot working medium through which a room area flows within a rotor arrangement of a turbomachine in the form of a heat accumulation unit the above-mentioned genus in such a way that preferably in the case of completely pre-assembled rotor disc arrangements, the subsequent Integration of a heat accumulation unit is possible which is state of the art does not have the listed disadvantages.
  • the heat accumulation unit should be possible to use the heat accumulation unit as a completely ring-shaped structure between two fixed pre-assembled rotor disks using an intimate but detachable joint bring in.
  • the heat accumulation unit should also be of the highest degree Tightness between the flow channel and the space facing the rotor allow to have minimal seal gaps and a mechanical stable and stress-optimized shape and geometry.
  • the invention is based on a device for separating one with a hot one Working medium flowing through a room area from a room area within a rotor arrangement of a fluid flow machine, preferably a gas turbine, the provides at least two rotor disks arranged axially one behind the other.
  • the rotor disks are firmly connected to one another via at least one connection area, for example by a welded joint, being in the area of their radial peripheral edges are spaced apart.
  • the flat heat accumulation unit has a toothed contour with web-shaped connecting elements and the connecting elements spaced spaces.
  • the heat accumulation unit (8) roughly corresponding toothed counter contour (13, 14) is provided such that the connecting elements (17) with the toothed counter contour can be brought into a form-fitting, releasably firm connection.
  • each individual connecting element is seen to be form-fitting Connect at least one molding section before that of the rest of the contour of the connecting element protrudes.
  • the mold section can be as Dovetail extension or in the simplest sense transverse to Be longitudinal extension of the connecting element bent.
  • each is in the area of the peripheral edge of the rotor disks, to the toothed contour the connecting edges of the heat accumulation unit approximately corresponding toothed Counter contour provided, with raised teeth, which each provide recesses, the exact fit of a counter contour corresponding to the shaped sections correspond.
  • the one based on the construction according to the invention can be used Use the joining mechanism for segmented heat accumulation units that are in angular series in a row around the circumferential edge of the rotor disks complete annular heat accumulation unit can be assembled.
  • the counter contour provided in the area of the peripheral edge of the rotor disks into which the connecting edges of the heat accumulation unit designed according to the invention can be used can either be worked directly into the material of the rotor disks be, but also in the foot area to be inserted in the peripheral edge of the rotor disks Blades are provided.
  • the heat accumulation unit has an axially circumferential counter contour corresponding curvature, the inner radius of which is approximately the outer radius the radially circumferential counter contour in the area of the peripheral edge of the rotor disk corresponds.
  • the tooth elements of the heat accumulation unit are axially aligned with the interdental spaces within the counter contours located in the area of the peripheral edges - via the Slide rotor disks and at a certain axial position in which the Formed sections of the tooth elements on the connecting edges of the heat accumulation unit angular with the recesses in the raised teeth within the counter contour align, by interlocking with the counter contour by rotating in the circumferential direction.
  • the shaped sections move precisely into the corresponding recesses the teeth contained in the opposite contour.
  • the heat accumulation unit is secured radially.
  • the heat accumulation unit can also provide additional fastening measures a further rotation in the circumferential direction are hindered, whereby the heat accumulation unit is securely fixed within the counter contour.
  • Locking pins prevent twisting in the circumferential direction of the heat accumulation unit help.
  • Figure 3 shows a schematic longitudinal section of a rotor arrangement through two Rotor disks 1, 2 are provided on their radial peripheral edge 3 rotor blades 4, 5 are.
  • a guide vane 12 protrudes between the rotor blades 4, 5.
  • Both rotor disks 1, 2 are permanently connected to one another via a weld seam 11 and rotate together around the axis of rotation A. In the peripheral area, close to their Circumferential edges see the rotor disks 1, 2 on opposite sides of the opposite contours 13, 14, into which the connecting edges 15, 16 protrude.
  • the counter contours are 13, 14 incorporated into the material of the rotor disks 1, 2, but it is also possible as mentioned above, that the counter contours are part of the blade roots. Combinations of both configurations are nevertheless also possible.
  • the rotor blade feet are positively connected to the rotor via an essentially axial Connection, e.g. fir tree connection, dovetail connection, connected.
  • an essentially axial Connection e.g. fir tree connection, dovetail connection
  • the counter contours 13, 14 and the connecting edges 15, 16 each have one serrated contour, which is designed to correspond to each other. So engages in illustrated case according to Figure 3, the connecting element 17 with its dovetail-like formed shaped section 18 into the corresponding recess 19th of the tooth 20 in the counter contour 13.
  • FIG 4 is a section of a perspective view of a section through the rotor disks 1 and 2 are shown, which are fixed to one another via a weld seam 11 are connected.
  • the rotor disk 1 has the counter contour 13 on the peripheral edge, which have a plurality of teeth 20 arranged side by side with teeth in between Interdental spaces 21 provides. The same applies to the counter contour 14 in the Rotor disc 2.
  • the teeth 20 have recesses 19, which are shown in the Provide a dovetail cutout example.
  • the heat accumulation unit is already in the assembled state between the rotor disks 1, 2 8 introduced, which has a curved flat shape.
  • Your connecting edges 15, 16 have toothed elements 17 which have a shaped section in the lower region 18 provide, which is designed in the manner of a dovetail.
  • the mold sections 18 sit in the cutouts 19 and secure on the basis their shape, the heat accumulation unit 8 radial direction.
  • the tooth elements 17 are axially opposite placed between the teeth 21 of the counter contours 13, 14 and in Axial direction between the rotor disks 1, 2 shifted.
  • the mold sections 18 are brought into register with the recesses 19, the heat accumulation unit 8 moved radially in the circumferential direction until the state shown in Figure 4 is reached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00810682A 1999-08-26 2000-07-31 Bouclier thermique pour un rotor de turbine Expired - Lifetime EP1079070B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19940525 1999-08-26
DE19940525A DE19940525A1 (de) 1999-08-26 1999-08-26 Wärmestaueinheit für eine Rotoranordnung

Publications (3)

Publication Number Publication Date
EP1079070A2 true EP1079070A2 (fr) 2001-02-28
EP1079070A3 EP1079070A3 (fr) 2004-01-14
EP1079070B1 EP1079070B1 (fr) 2005-03-16

Family

ID=7919697

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810682A Expired - Lifetime EP1079070B1 (fr) 1999-08-26 2000-07-31 Bouclier thermique pour un rotor de turbine

Country Status (2)

Country Link
EP (1) EP1079070B1 (fr)
DE (2) DE19940525A1 (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1264964A1 (fr) * 2001-06-07 2002-12-11 Snecma Moteurs Agencement de rotor de turbomachine à deux disques aubages séparés par une entretoise
WO2007023158A1 (fr) * 2005-08-23 2007-03-01 Alstom Technology Ltd Dispositif pour securiser le montage d'un element de protection thermique destine a une unite rotor d'une turbomachine et fixer cet element
EP1898054A1 (fr) * 2006-08-25 2008-03-12 ALSTOM Technology Ltd Turbine à gaz
CN101845996A (zh) * 2009-01-14 2010-09-29 通用电气公司 用于在燃气轮机中减少二次空气流的装置和系统
CN101852100A (zh) * 2009-03-24 2010-10-06 通用电气公司 用于涡轮级间密封环的方法和设备
CN101858257A (zh) * 2009-04-02 2010-10-13 通用电气公司 燃气涡轮机内部流径遮盖件
WO2012056161A1 (fr) * 2010-10-28 2012-05-03 Snecma Ensemble de disques de rotor pour une turbomachine
EP2218879A3 (fr) * 2009-02-13 2012-12-05 General Electric Company Ensemble de rotors avec joint entre les étages
EP2832952A1 (fr) 2013-07-31 2015-02-04 ALSTOM Technology Ltd Aube de turbine et turbine à étanchéité améliorée
EP2930304A1 (fr) * 2014-04-11 2015-10-14 United Technologies Corporation Compresseur à haute pression avec appareil et système de bouclier thermique
EP3168205A1 (fr) 2015-11-12 2017-05-17 General Electric Technology GmbH Pièce de turbine à gaz et procédé de fabrication d'un tel élément de turbine à gaz
FR3057016A1 (fr) * 2016-09-30 2018-04-06 Safran Aircraft Engines Procede de conception d'un organe de rotor et organe de rotor ameliore
EP3318724A1 (fr) * 2016-11-04 2018-05-09 Siemens Aktiengesellschaft Segment d'étanchéité d'un rotor et rotor
DE102017220336A1 (de) * 2017-11-15 2019-05-16 Siemens Aktiengesellschaft Dichtsegment eines Rotors sowie Rotor
EP3078809B1 (fr) 2015-04-10 2019-07-03 United Technologies Corporation Joint labyrinthe rotatif ayant la forme d'un m
WO2020025406A1 (fr) * 2018-08-02 2020-02-06 Siemens Aktiengesellschaft Rotor pourvu d'une pièce disposée entre deux disques de rotor
US10612382B2 (en) 2015-11-12 2020-04-07 Ansaldo Energia Ip Uk Limited Method for manufacturing gas turbine part
FR3120894A1 (fr) * 2021-03-19 2022-09-23 Safran Aircraft Engines Rotor de turbomachine, comprenant un anneau de joint a labyrinthe monte sur des viroles de disque
CN117722235A (zh) * 2024-02-18 2024-03-19 中国航发四川燃气涡轮研究院 双辐板涡轮盘

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE950100C (de) * 1955-04-10 1956-10-04 Maschf Augsburg Nuernberg Ag Zusammengesetzter Trommellaeufer fuer Kreiselmaschinen, insbesondere fuer Gasturbinen mit axialer Durchstroemrichtung
GB848465A (en) * 1957-06-14 1960-09-14 Napier & Son Ltd Rotors of multi-stage axial flow compressors or turbines
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
JP2941698B2 (ja) * 1995-11-10 1999-08-25 三菱重工業株式会社 ガスタービンロータ
WO1998057040A1 (fr) * 1997-06-11 1998-12-17 Mitsubishi Heavy Industries, Ltd. Rotor pour turbines a gaz

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1264964A1 (fr) * 2001-06-07 2002-12-11 Snecma Moteurs Agencement de rotor de turbomachine à deux disques aubages séparés par une entretoise
FR2825748A1 (fr) * 2001-06-07 2002-12-13 Snecma Moteurs Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise
US6655920B2 (en) 2001-06-07 2003-12-02 Snecma Moteurs Turbomachine rotor assembly with two bladed-discs separated by a spacer
WO2007023158A1 (fr) * 2005-08-23 2007-03-01 Alstom Technology Ltd Dispositif pour securiser le montage d'un element de protection thermique destine a une unite rotor d'une turbomachine et fixer cet element
US7722319B2 (en) 2005-08-23 2010-05-25 Alstom Technology Ltd Locking and fixing device for a heat shield element for a rotor unit of a turbomachine
EP1898054A1 (fr) * 2006-08-25 2008-03-12 ALSTOM Technology Ltd Turbine à gaz
US8182211B2 (en) 2006-08-25 2012-05-22 Alstom Technology Ltd. Turbo machine
CN101845996A (zh) * 2009-01-14 2010-09-29 通用电气公司 用于在燃气轮机中减少二次空气流的装置和系统
CN101845996B (zh) * 2009-01-14 2015-04-01 通用电气公司 用于在燃气轮机中减少二次空气流的装置和系统
EP2208860A3 (fr) * 2009-01-14 2012-12-05 General Electric Company Joint entre étages de turbine à gaz et turbine à gaz associée
EP2218879A3 (fr) * 2009-02-13 2012-12-05 General Electric Company Ensemble de rotors avec joint entre les étages
CN101852100A (zh) * 2009-03-24 2010-10-06 通用电气公司 用于涡轮级间密封环的方法和设备
EP2236769A3 (fr) * 2009-03-24 2014-02-19 General Electric Company Procédé et appareil pour bague d'étanchéité inter-étages de turbine
CN101858257A (zh) * 2009-04-02 2010-10-13 通用电气公司 燃气涡轮机内部流径遮盖件
EP2236767A3 (fr) * 2009-04-02 2014-04-23 General Electric Company Elément de recouvrement de la paroi interne du canal d'écoulement d'une turbine à gaz
WO2012056161A1 (fr) * 2010-10-28 2012-05-03 Snecma Ensemble de disques de rotor pour une turbomachine
FR2966867A1 (fr) * 2010-10-28 2012-05-04 Snecma Ensemble de disques de rotor pour une turbomachine
US9371742B2 (en) 2010-10-28 2016-06-21 Snecma Set of rotor disks for a turbine engine
GB2498321A (en) * 2010-10-28 2013-07-10 Snecma Set of rotor discs for a turbomachine
GB2498321B (en) * 2010-10-28 2017-07-05 Snecma A set of rotor disks for a turbine engine
EP2832952A1 (fr) 2013-07-31 2015-02-04 ALSTOM Technology Ltd Aube de turbine et turbine à étanchéité améliorée
US9816393B2 (en) 2013-07-31 2017-11-14 Ansaldo Energia Ip Uk Limited Turbine blade and turbine with improved sealing
US10036278B2 (en) 2014-04-11 2018-07-31 United Technologies Corporation High pressure compressor thermal shield apparatus and system
EP2930304A1 (fr) * 2014-04-11 2015-10-14 United Technologies Corporation Compresseur à haute pression avec appareil et système de bouclier thermique
EP3078809B1 (fr) 2015-04-10 2019-07-03 United Technologies Corporation Joint labyrinthe rotatif ayant la forme d'un m
US10570742B2 (en) 2015-11-12 2020-02-25 Ansaldo Energia Ip Uk Limited Gas turbine part and method for manufacturing such gas turbine part
EP3168205A1 (fr) 2015-11-12 2017-05-17 General Electric Technology GmbH Pièce de turbine à gaz et procédé de fabrication d'un tel élément de turbine à gaz
US10612382B2 (en) 2015-11-12 2020-04-07 Ansaldo Energia Ip Uk Limited Method for manufacturing gas turbine part
FR3057016A1 (fr) * 2016-09-30 2018-04-06 Safran Aircraft Engines Procede de conception d'un organe de rotor et organe de rotor ameliore
WO2018082907A1 (fr) * 2016-11-04 2018-05-11 Siemens Aktiengesellschaft Segment étanche d'un rotor et rotor
EP3318724A1 (fr) * 2016-11-04 2018-05-09 Siemens Aktiengesellschaft Segment d'étanchéité d'un rotor et rotor
DE102017220336A1 (de) * 2017-11-15 2019-05-16 Siemens Aktiengesellschaft Dichtsegment eines Rotors sowie Rotor
WO2020025406A1 (fr) * 2018-08-02 2020-02-06 Siemens Aktiengesellschaft Rotor pourvu d'une pièce disposée entre deux disques de rotor
US11339662B2 (en) 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
FR3120894A1 (fr) * 2021-03-19 2022-09-23 Safran Aircraft Engines Rotor de turbomachine, comprenant un anneau de joint a labyrinthe monte sur des viroles de disque
CN117722235A (zh) * 2024-02-18 2024-03-19 中国航发四川燃气涡轮研究院 双辐板涡轮盘
CN117722235B (zh) * 2024-02-18 2024-05-17 中国航发四川燃气涡轮研究院 双辐板涡轮盘

Also Published As

Publication number Publication date
EP1079070B1 (fr) 2005-03-16
DE50009768D1 (de) 2005-04-21
EP1079070A3 (fr) 2004-01-14
DE19940525A1 (de) 2001-03-01

Similar Documents

Publication Publication Date Title
EP1079070A2 (fr) Bouclier thermique pour un rotor de turbine
DE69005845T2 (de) Diaphragmaaufbau eines Verdichters.
DE859089C (de) Beschaufelte, von einem Arbeitsmittel durchstroemte Kreiselmaschine
DE69516423T2 (de) Dichtsteifenanordnung für gasturbinenstahltriebwerke
DE3825951C2 (de) Einsatzelement
EP1180196B1 (fr) Turbomachine comportant un systeme d'etancheite pour un rotor
EP1199440B1 (fr) Segments d'anneau statorique à connection par bride
EP1183444B1 (fr) Turbomachine ainsi qu'element d'etancheite pour un rotor d'une turbomachine
EP3409897B1 (fr) Agencement d'étanchéité pour une turbomachine, méthode de fabrication de l'agencement d'étanchéité et turbomachine
EP1451450B1 (fr) Ensemble turbine a gaz
DE3008889A1 (de) Beschaufelter rotor fuer ein gasturbinentriebwerk
DE19615549B4 (de) Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
EP1848904B1 (fr) Element d'etancheite s'utilisant dans une turbomachine
EP1022437A1 (fr) Elément de construction à l'usage d'une machine thermique
DE102014118013A1 (de) Turbinenschaufelabschlussanordnung und Verfahren zur Montage derselben
EP0745756B1 (fr) Dispositif et méthode de montage d'aubes de rotor
DE3924829C2 (fr)
DE102014114555A1 (de) Verriegelnde Abstandshalteranordnung
EP0909924B1 (fr) Suspension d'une chambre de combustion annulaire de turbine à gaz
DE2140816A1 (de) Rotor fuer stroemungsmaschinen
DE19914227A1 (de) Wärmeschutzvorrichtung in Gasturbinen
EP2378066A2 (fr) Rotor pour une turbomachine
DE19654471B4 (de) Rotor einer Strömungsmaschine
DE2555911A1 (de) Rotor fuer stroemungsmaschinen, insbesondere gasturbinenstrahltriebwerke
CH195736A (de) Turbinenrotor mit wenigstens einem Schaufelrad.

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: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

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

Owner name: ALSTOM

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

Owner name: ALSTOM (SWITZERLAND) LTD

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

RIC1 Information provided on ipc code assigned before grant

Ipc: 7F 01D 5/06 A

Ipc: 7F 01D 5/06 B

Ipc: 7F 01D 11/00 B

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

Owner name: ALSTOM TECHNOLOGY LTD

17P Request for examination filed

Effective date: 20040705

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

AKX Designation fees paid

Designated state(s): DE GB

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): DE GB

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: IE

Ref legal event code: FG4D

Free format text: GERMAN

REF Corresponds to:

Ref document number: 50009768

Country of ref document: DE

Date of ref document: 20050421

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050606

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: 20051219

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

Ref country code: DE

Payment date: 20060714

Year of fee payment: 7

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

Ref country code: GB

Payment date: 20060720

Year of fee payment: 7

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

Effective date: 20070731

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: 20080201

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: 20070731