EP2888448A1 - Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type - Google Patents

Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type

Info

Publication number
EP2888448A1
EP2888448A1 EP13763011.7A EP13763011A EP2888448A1 EP 2888448 A1 EP2888448 A1 EP 2888448A1 EP 13763011 A EP13763011 A EP 13763011A EP 2888448 A1 EP2888448 A1 EP 2888448A1
Authority
EP
European Patent Office
Prior art keywords
rotor
connecting means
components
section
abutment
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.)
Withdrawn
Application number
EP13763011.7A
Other languages
German (de)
English (en)
Inventor
Karin COSTAMAGNA
Sascha Dungs
Harald Hoell
Henrik Hull
Karsten Kolk
Ulf LAUDAGE
Harald Nimptsch
Peter Schröder
Vyacheslav Veitsman
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
Publication of EP2888448A1 publication Critical patent/EP2888448A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D5/02—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
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a rotor for an axially flow-through turbomachine, comprising a number of a plurality of disk-shaped or drum-shaped rotor components and at least one extending through the rotor components tie rod, at the protruding ends in each case an abutment for axially clamping the rotor components arranged therebetween is screwed.
  • the invention relates to a method for assembling and releasing such a rotor.
  • Such rotors are well known from the extensive existing state of the art to stationary gas turbines.
  • the rotor is designed in a so-called disc design, the rotor disks on its outer periphery blades, either for the compressor or for the turbine unit
  • a central hollow shaft as a drum-shaped component is arranged between the compressor disks and turbine disks.
  • a central tension anchor extends through all the rotor components, the rotor components being arranged between these two hollow shafts with the aid of two counter bearings, the front hollow shaft and the rear hollow shaft
  • the tie rod is elastically stretched to its yield point, whereby the individual rotor components are clamped together.
  • a similar construction is also possible with decentralized tie rods, wherein lying on an equal radius, for example, twelve tie rods are arranged distributed equal. It is also known to weld the disc-shaped or drum-shaped rotor components together. Even combinations of the aforementioned embodiments, in which, for example, the compressor rotor is welded and the
  • Rotor components of the turbine unit are clamped by a screw with bolts on the circumference, are also known.
  • the object of the invention is to specify an alternative design of rotors for an axially flow-through turbomachine. Another object of the invention is to provide the method required for assembling and disassembling such a rotor.
  • Rotor components called - clamped between a first abutment and a connecting means are screwed onto a tie rod until all of the first rotor components arranged therebetween are pressed firmly against one another by the two.
  • those rotor components which are to be assigned to a second rotor section are then Generally referred to as second rotor components -, threaded on the tie rod connection side.
  • a second abutment is screwed, with the help of the second rotor components and the first rotor components between the two abutments are braced.
  • the tension then separates between the first thrust bearing and the connecting means, so that at the end of the assembly of the rotor, the connecting means is only slightly or no longer involved in any tensioning. All rotor components are then braced clamped by the two thrust bearings in conjunction with the tie rod.
  • the process steps are then of course carried out in reverse order, so that first a second rotor section with second disc-shaped rotor components by loosening the screwed on the tie rod second abutment is relaxed to disassemble the braced disc-shaped rotor components comprehensive rotor of an axially flowable turbomachine, said meanwhile, the first disk-shaped rotor components of the first rotor section are clamped between the first counter bearing and a connecting means screwed onto the tie rod.
  • the rotor comprises a number of disc-shaped or drum-shaped rotor components and at least one extending through the rotor components through tie rods, at its protruding ends in each case an abutment for axially clamping the rotor components arranged therebetween is screwed, wherein screwed between the two abutments a connecting means on the tie rod is, in such a way that after loosening one of the two abutment which are arranged between the connecting means and the other of the two abutment rotor components of the connecting means and the other abutment braced.
  • the rotor comprises along its longitudinal extent a first rotor end section, at least one further rotor section and a second rotor end section, wherein the connecting means is arranged axially in one of the further rotor sections.
  • the first rotor section defined for the method comprises the first rotor end section and the further rotor section, whereas the second rotor section corresponds to the second rotor end section.
  • the connecting means and one of the rotor components are configured such that after loosening of the arranged on the second rotor end portion abutment means adjacent to the second rotor end portion connecting means with the arranged on the first rotor end abutment the intermediate rotor components with each other.
  • a particular advantage of this embodiment is that, in a first assembly step, the rotor components threaded onto the first tie rod element can already be braced by one of the two counter bearings and the connecting means, although the rotor is not yet completely equipped with rotor components. Only then are the other disc-shaped or drum-shaped
  • the tension which in the meantime acts on one part of the disk-shaped or drum-shaped rotor components from one of the two counter bearings and the connecting element, is thereby released again.
  • the preliminary and final distortions are matched to one another in such a way that, with the final clamping of the rotor components between the two counter bearings, the initial tensioning of counter bearing and connecting element is at least partially, but preferably completely, released.
  • the connecting means is designed as a nut.
  • the connecting element is monolithically connected to the tie rod.
  • the connecting means has a plurality of openings for the passage of a fluid from one of the rotor (end) sections to another of the rotor (end) sections.
  • the respective connecting means has a circumferentially arranged circumferential shaft collar by the openings are arranged as passage openings for cooling fluid.
  • the connecting means can also be used to realize a support of the tie rod to reduce vibrations during operation of the turbomachine.
  • the connecting means can also be used to realize a support of the tie rod to reduce vibrations during operation of the turbomachine.
  • the rotor is designed as a gas turbine rotor, the first rotor end portion as a compressor rotor, the further rotor portion as a central rotor portion and the second Rotorendab- cut as a turbine rotor.
  • the central rotor section may be formed solely by a hollow shaft or by a plurality of blade-less rotor disks and the rotor end sections by rotor disks.
  • the invention is based on embodiments in the
  • FIG. 1 shows a partial longitudinal section through a rotor according to the invention for a stationary axial flow turbine engine
  • Figure 2 shows a detail of the longitudinal section of FIG
  • FIG. 3 shows the same section of Figure 2, according to an alternative embodiment
  • Figure 4 shows a connecting element with a circumferentially arranged shaft collar
  • FIG. 5 shows a perspective view of the connecting element according to FIG. 4 and FIG. 6 shows a connecting element radially supporting on the rotor component, in a longitudinal section according to FIG. 2.
  • the rotor 10 is designed as a gas turbine rotor, wherein the remaining components of the gas turbine are not shown here.
  • the design of the rotor 10 is fundamentally modular and can be described as a disk construction.
  • the rotor 10 comprises a number of rotor disks 12, which are also referred to here as disc-shaped rotor components 14.
  • the rotor 10 also includes a drum-shaped rotor component 16, which is referred to in the embodiment as a central hollow shaft 18.
  • a front hollow shaft 22 screwed onto a tie rod 20 and a rear hollow shaft 24 screwed on the opposite end.
  • the front hollow shaft 22 is also referred to here as the first counter bearing 26 and the rear hollow shaft 24 as the second counter bearing 28 ,
  • the two abutments 26, 28 clamp with the help of the tie rod 20, the rotor components 14, 16 with each other and press them firmly together. To achieve this, the tie rod 20 of the two abutments 26, 28 stretched elastically.
  • a connecting means 34 designed as a screw nut 35 is screwed on the tie rod 20 in the interior of the rotor 10 in order to clamp the rotor components 14, 16 arranged in a section of the rotor 10 during the assembly or disassembly of the rotor alone.
  • the rotor 10 can theoretically be axially divided into a first rotor end section 38, into a further rotor section 40 and into a second rotor end section 42, wherein the
  • Connecting means 34 is arranged axially seen in the other rotor section 40.
  • the first rotor end section 38 is designed as a compressor rotor 44, and the second rotor end section 42 as a turbine rotor 48.
  • a combustion chamber of the gas turbine is arranged radially outside the rotor 10.
  • FIGS. 2 to 4 show a section from the transition region between the further rotor section 40 and the second rotor end section 42 in a longitudinal section.
  • the nut 35 is screwed as a connecting means 34.
  • Radially adjacent to the nut 35 the middle hollow shaft 18 is arranged.
  • the nut 35 has a conical surface 50, whose pitch corresponds to an inwardly facing surface 52 of the central hollow shaft 18.
  • a smaller shaft collar 54 is provided centrally between the two screw-in openings 37 of the nuts 35, the side surface 56 of which bears against a side surface 58 of the central hollow shaft 18 parallel thereto.
  • the first abutment 26 is first screwed onto the tie rod 20 on the end side. Subsequently, this assembly is placed vertically, so that the individual disk-shaped or drum-shaped rotor components 14, 16 can be deposited from above onto the first counter-bearing 26. Subsequently, the screw nut 35 is screwed onto the still free end of the tie rod element 30 until the rotor components 14, 16 lying between the screw nut 35 and the first abutment 26 are clamped together. Subsequently, the rotor disks 12 provided for the turbine rotor 48 are threaded onto the turbine-side end of the tie rod 20 from above and laid down.
  • the second abutment 28 is screwed onto the still free end of the tie rod 20.
  • the entire tie rod 20 is elastically stretched so that the tension of the nut 35th or the connecting means 34 and the first abutment 26 dissolves again.
  • axially extending holes 60 may be provided both in the central hollow shaft 18 and in the nut 35, with which a coolant from a rotor (end) section to another rotor (end) section can be passed.
  • FIG. 3 shows the same section as FIG. 2, but with the construction for axial clamping in the region of FIG.
  • Nut 35 and the central hollow shaft 18 is slightly modified compared to the construction of FIG 2. The required for the establishment of the axial tension radial overlap of nut 35 and middle
  • Hollow shaft 18 takes place here using an interposed sleeve provided with a collar 62nd
  • FIG. 4 shows a further exemplary embodiment for bracing the rotor components 14, 16 between a first counter bearing (not shown in FIG. 4) and the connecting means 34.
  • the connecting means 34 is designed again as a screw nut 35 with two screw holes 37 located opposite one another.
  • a larger shaft collar 54 is provided on the outer circumference, in which circumferentially uniformly distributed openings 64 are provided for the passage of a cooling fluid.
  • the two parallel side surfaces 56 of the shaft collar 54 go over a radius in curved sloping edges 57, which end at the screw-37.
  • This nut 35 with the screw-in opening 37 and four uniformly distributed passage openings 64 is shown in FIG 5 in perspective view.
  • a circumferential groove 66 with a support wire 68 located therein may be provided on the shell-side surface of the shaft collar 54, with the aid of which the tie rod 20 itself radially on one of the rotor components, according to FIG 6 on the central hollow shaft 18, supported.
  • FIGS. 2 to 6 mean that they show gas turbine rotors 10 in which the second counterbearing 28 has not yet been screwed onto the second tie rod element 32, so that only those to the left of the screw nut 35 in FIGS shown
  • Rotor components 14, 16 are clamped to the first abutment 26 and the rotor components 14, 16 shown to the right thereof not.
  • the invention thus relates to a rotor 10 for an axially flow-through turbomachine, comprising a number of several disk-shaped or drum-shaped
  • connection means 34 is screwed onto the tie rod 20 between the two counter bearings 26, 28, by means of which

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un rotor (10) pour une turbomachine à écoulement axial, comprenant une pluralité d'éléments de rotor en forme de disques (12) ou de tambours (16) et au moins un tirant (20) en forme de tige qui s'étend à travers les éléments de rotor (14) et sur chaque extrémité en saillie duquel est vissée une butée (26, 28) destinée au serrage axial des éléments de rotor (14) disposés dans l'espace intermédiaire. L'invention vise à créer un rotor (10) qui permette de raccourcir les intervalles de maintenance. A cet effet, un moyen de liaison (34) est vissé sur le tirant (20) entre les deux butées (26, 28), ce moyen de liaison (34) permettant, lorsqu'une des deux butées (28) est desserrée, de serrer ensemble les éléments de rotor (12,14) disposés entre le moyen de liaison (34) et l'autre butée (26).
EP13763011.7A 2012-09-07 2013-09-06 Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type Withdrawn EP2888448A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012215886 2012-09-07
PCT/EP2013/068507 WO2014037523A1 (fr) 2012-09-07 2013-09-06 Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type

Publications (1)

Publication Number Publication Date
EP2888448A1 true EP2888448A1 (fr) 2015-07-01

Family

ID=49182221

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13763011.7A Withdrawn EP2888448A1 (fr) 2012-09-07 2013-09-06 Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type
EP13762773.3A Withdrawn EP2880264A1 (fr) 2012-09-07 2013-09-06 Rotor pour une turbomachine à écoulement axial et double écrou destine à relier deux éléments de tirant

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13762773.3A Withdrawn EP2880264A1 (fr) 2012-09-07 2013-09-06 Rotor pour une turbomachine à écoulement axial et double écrou destine à relier deux éléments de tirant

Country Status (12)

Country Link
US (2) US20150247406A1 (fr)
EP (2) EP2888448A1 (fr)
JP (2) JP2015528539A (fr)
KR (2) KR20150047508A (fr)
CN (2) CN104603396B (fr)
BR (2) BR112015004983A2 (fr)
CA (2) CA2884133A1 (fr)
IN (2) IN2015DN00890A (fr)
MX (1) MX2015002944A (fr)
RU (2) RU2015109757A (fr)
SA (2) SA515360111B1 (fr)
WO (2) WO2014037523A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927425A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Rotor de turbine à gaz avec dispositif anti-rotation pour un écrou d'arbre
EP2980354A1 (fr) * 2014-07-30 2016-02-03 Siemens Aktiengesellschaft Rotor d'une turbine à gaz et turbine à gaz associée
RU2567887C1 (ru) * 2014-08-08 2015-11-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Ротор компрессора газотурбинного двигателя
DE102014220294A1 (de) 2014-10-07 2016-04-07 Siemens Aktiengesellschaft Spannsystem zum Vorspannen eines Zugangs einer Strömungskraftmaschine
DE102015225428A1 (de) * 2015-12-16 2017-07-06 Siemens Aktiengesellschaft Läufer für eine Strömungsmaschine
IT201600123382A1 (it) * 2016-12-05 2018-06-05 Ansaldo Energia Spa Metodo e dispositivo per controllare il posizionamento di almeno un disco rotorico attorno ad un tirante di un rotore di una turbina a gas
US11131195B2 (en) * 2019-03-14 2021-09-28 Raytheon Technologies Corporation Tie shaft assembly for a gas turbine engine
US11105204B2 (en) 2019-06-11 2021-08-31 Pratt & Whitney Canada Corp. Turbine assembly

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090067947A1 (en) * 2006-11-17 2009-03-12 Mitsubishi Heavy Industries, Ltd. Fastening device
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB308260A (en) * 1928-03-20 1930-06-16 Albert Paul Streit Improvements in locking stretchers for tensioning wires and the manufacture thereof
US3970398A (en) * 1975-08-04 1976-07-20 United Technologies Corporation Shaft coupling
JPS6058680U (ja) * 1983-09-29 1985-04-24 ジャパンライフ株式会社 プラグとソケット
FR2640014A1 (fr) * 1988-12-01 1990-06-08 Linz Emile Tendeur de cables
US5454662A (en) * 1993-11-23 1995-10-03 Animal Enclosure Systems Connector for coupling the pipes of a pipe corral
JP3733573B2 (ja) * 1995-03-03 2006-01-11 石川島播磨重工業株式会社 ガスタービンとその組立方法
JPH10325491A (ja) * 1997-05-26 1998-12-08 Nippon Yuuki Kk 配管接続部品
US7409819B2 (en) * 2004-10-29 2008-08-12 General Electric Company Gas turbine engine and method of assembling same
US7584621B2 (en) * 2005-08-05 2009-09-08 Siemens Energy, Inc. Radially expanding turbine engine exhaust cylinder interface
DE102005052819A1 (de) * 2005-11-05 2007-05-10 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
US7775779B2 (en) * 2005-11-17 2010-08-17 Sclumberger Technology Corporation Pump apparatus, systems and methods
EP1970530A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor d'une turbomachine thermique et turbomachine thermique
US8186939B2 (en) * 2009-08-25 2012-05-29 Pratt & Whitney Canada Corp. Turbine disc and retaining nut arrangement
EP2415967A1 (fr) * 2010-08-03 2012-02-08 Siemens Aktiengesellschaft Moteur à turbine à gaz comprenant un mécanisme appliquant la tension
US8794923B2 (en) * 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
ITCO20130071A1 (it) * 2013-12-18 2015-06-19 Nuovo Pignone Srl Metodo per assemblare un insieme di giranti mediante tiranti, girante e turbomacchina

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090067947A1 (en) * 2006-11-17 2009-03-12 Mitsubishi Heavy Industries, Ltd. Fastening device
GB2452932A (en) * 2007-09-19 2009-03-25 Siemens Ag Turbine or turbomachine with axial shaft-mounted compressor and turbine blades

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2014037523A1 *

Also Published As

Publication number Publication date
SA515360112B1 (ar) 2015-12-20
IN2015DN01253A (fr) 2015-06-26
CN104603396A (zh) 2015-05-06
CN104603396B (zh) 2016-08-24
CN104619954B (zh) 2016-08-24
WO2014037523A1 (fr) 2014-03-13
EP2880264A1 (fr) 2015-06-10
CA2884126A1 (fr) 2014-03-13
BR112015004983A2 (pt) 2017-07-04
KR20150047508A (ko) 2015-05-04
RU2015112596A (ru) 2016-10-27
CA2884133A1 (fr) 2014-03-13
IN2015DN00890A (fr) 2015-06-12
US20150247406A1 (en) 2015-09-03
MX2015002944A (es) 2015-06-02
RU2015109757A (ru) 2016-10-27
BR112015004993A2 (pt) 2017-07-04
KR20150047509A (ko) 2015-05-04
WO2014037521A1 (fr) 2014-03-13
JP2015527534A (ja) 2015-09-17
CN104619954A (zh) 2015-05-13
JP2015528539A (ja) 2015-09-28
SA515360111B1 (ar) 2016-02-24
US20150260044A1 (en) 2015-09-17

Similar Documents

Publication Publication Date Title
WO2014037523A1 (fr) Procédé permettant d'assembler ou de désassembler un rotor comportant une pluralité d'éléments de rotor pour une turbomachine à écoulement axial et rotor de ce type
EP2011965B1 (fr) Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction
EP1825141B1 (fr) Eolienne comprenant un dispositif de maintien pour un arbre de rotor
EP2845999B1 (fr) Procédé d'équilibrage et de montage d'un rotor de turbine
EP3092371B1 (fr) Rotor doté d'une bague d'appui bloquée axialement
WO2012100933A1 (fr) Procédé et dispositif pour remplacer une plaque d'étanchéité dans un moteur d'avion
WO2007051443A1 (fr) Turbomoteur dote d'un tirant d'ancrage constitue de douilles de traction et de poussee
DE3219006C2 (de) Laufrad einer Strömungsmaschine
EP3122999B1 (fr) Écrou de serrage annulaire pour tirant
EP2255071B1 (fr) Rotor de turbine à gaz
EP3204187B1 (fr) Procédé de montage d'aubes rotoriques sur un disque de rotor et tensionneur associé destiné à mettre en oeuvre un tel procédé
EP2352905B1 (fr) Dispositif d'assemblage avec un tirant d'ancrage et procédé correspondant pour un système rotorique d'une turbomachine axiale
EP3337958B1 (fr) Rotor pour une turbomachine
EP2522819B1 (fr) Fixation d'un disque de palier axial dans une turbomachine à palier magnétique au moyen d'une frette de serrage
WO2012003908A1 (fr) Disque de frein et procédé de montage
DE60215327T2 (de) Turbinen- oder kompressorvorrichtung und verfahren zur montage der vorrichtung
CH709983B1 (de) Abgasturbolader.
DE102004016244B4 (de) Rotor für eine Turbomaschine
EP3179169B1 (fr) Procédé de montage d'une chambre de combustion d'une turbine à gaz
EP3064705B1 (fr) Rotor doté d'une tôle de sûreté destiné à protéger un verrouillage rotatif contre le dévissage
EP1862638B1 (fr) Procédé pour la réparation d'un rotor d'une turbine à gaz et rotor d'une turbine à gaz
DE102018106135B4 (de) Führungsvorrichtung
WO2010089125A2 (fr) Élément annulaire de guidage pour turbines et procédé de fabrication correspondant
EP3128128A1 (fr) Rotor boulonné pour une turbomachine, en particulier turbine à vapeur
DE102015224988A1 (de) Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks

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: 20150120

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL 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 RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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

Effective date: 20160704

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20161115