EP2860351A1 - Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor - Google Patents

Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor Download PDF

Info

Publication number
EP2860351A1
EP2860351A1 EP20130187993 EP13187993A EP2860351A1 EP 2860351 A1 EP2860351 A1 EP 2860351A1 EP 20130187993 EP20130187993 EP 20130187993 EP 13187993 A EP13187993 A EP 13187993A EP 2860351 A1 EP2860351 A1 EP 2860351A1
Authority
EP
European Patent Office
Prior art keywords
rotor
cover plate
blade
web
securing
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Withdrawn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
EP20130187993
Other languages
German (de)
English (en)
Inventor
Sascha Dr. Dungs
Karsten Dr. Kolk
Peter Schröder
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP20130187993 priority Critical patent/EP2860351A1/fr
Priority to CN201480055798.8A priority patent/CN105637183B/zh
Priority to EP14759178.8A priority patent/EP3019706B1/fr
Priority to PCT/EP2014/068825 priority patent/WO2015051956A1/fr
Priority to US15/025,589 priority patent/US10132173B2/en
Publication of EP2860351A1 publication Critical patent/EP2860351A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2240/80—Platforms for stationary or moving 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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

Definitions

  • the invention relates to an arrangement for securing a functional position of a arranged on an outer circumference of a rotor of a rotor of a gas turbine cover plate of the rotor relative to a arranged on the outer circumference of the rotor disk rotor blade, wherein between the cover plate located in its functional position and one of the cover plate side facing a blade root of the blade, a channel portion of an annular cooling channel of the rotor is formed.
  • the invention further relates to a rotor assembly of a rotor of a gas turbine, comprising a rotor disk, a rotor blade arranged on the outer circumference of the rotor disk, a cover plate ring arranged on the outer circumference of the rotor disk.
  • the invention relates to a rotor for a gas turbine and a gas turbine.
  • This functional position of the blocking element is ensured that the blocking element engages in a certain rotational position relative to the cover plate the edge of the opening blade end side by means of a cam formed on the blocking element and that the blocking element located in this rotational position is secured against rotation relative to the cover plate about a longitudinal axis of the blocking element. Securing the rotational position of the blocking element is achieved in that a part of the blocking element is plastically deformed and thereby engages in a beard opening of the keyhole-like opening.
  • the object of the invention is to provide a novel and easy way to secure functional positions of arranged on an outer circumference of a rotor of a rotor of a gas turbine cover plates of the rotor relative to arranged on the outer circumference of the rotor disc rotor blades of the rotor.
  • the functional position of the cover plate is secured when the securing bolt extends partially in the formed on the guide portion of the cover plate guide opening and the web is at least partially disposed in the recesses. This is effected in particular by the fact that the web extends radially with respect to the rotor disk when the rotor blade is arranged on the rotor disk.
  • the formed on the cover plate thickening or the guide portion formed thereby allows the formation of a longer guide opening and thereby a good leadership of the locking bolt.
  • the thickening or the guide section due to the thickening or the guide section, forces occurring during operation of a correspondingly formed gas turbine can be better absorbed by the cover plate due to the contact with the securing bolt in the region of the guide opening, without damaging the cover plate, in particular in the region of the guide opening. comes.
  • the guide portion completely surrounds the guide opening.
  • the fact that the outer diameter of the securing bolt corresponds to the diameter of the guide opening is intended to mean that the securing bolt can be inserted in a form-fitting manner into the guide opening.
  • the open towards the end of the locking bolt training and diametrical arrangement of the recesses allows simultaneous insertion of the web in the two recesses by the locking pin is placed on the bridge.
  • the width of the recesses is preferably equal to the width of the web.
  • the safety device for securing a functional position of the safety bolt on the cover plate and the blade keeps the safety pin permanently secure in its plugged onto the web position, d. H. in its functional position.
  • the securing device may be designed in any manner suitable for this purpose.
  • the inventive arrangement can be realized in the course of retrofitting an existing gas turbine.
  • the arrangement can already be taken into account in a new development of gas turbines.
  • various types of gas turbines can be equipped.
  • an arrangement according to the invention is provided for each cover plate of a rotor.
  • the securing bolt and / or the web are formed of metal and may be hardened to reduce wear on these components in a suitable manner.
  • the securing device preferably comprises a groove arranged on the side of the guide section facing the blade root, which extends radially from the guide opening over at least part of the guide section, and an L-shaped, plastically deformable securing wire, wherein the diameter of the longitudinal bore of the securing bolt Width of the groove and the width of the recesses are greater than or equal to the outer diameter of the safety wire.
  • One leg of the L-shaped safety wire can thus be arranged in the longitudinal bore of the partially in the guide opening on the cover plate Fuse bolt are introduced until the other leg of the fuse wire is at least partially in the groove formed on the guide portion.
  • the safety pin is secured relative to the cover plate against rotation about its longitudinal axis.
  • the diameter of the longitudinal bore, the width of the groove and the width of the recesses are preferably equal to the outer diameter of the safety wire, so that appropriate form fit between components of the assembly can be produced.
  • a recess is preferably formed by a predetermined length difference longer than the other recess, wherein the difference in length is greater than or equal to the outer diameter of the safety wire.
  • the difference in length is equal to the outer diameter of the safety wire.
  • the length of the shorter recess may, for example, correspond to the height of the web, whereas the length of the longer recess may correspond to the sum of the height of the web and the outside diameter of the safety wire.
  • the recesses may alternatively be designed to be of equal length.
  • the web is preferably formed monolithically with the blade.
  • the web for example, can be produced inexpensively together with the remaining blade in a casting process. As a result, a very robust connection between the web and the remaining blade is created. Alternatively, the web can be made separately and then connected to the blade.
  • the web is arranged on a formed on the cover plate side facing the blade root return.
  • axial space can be saved to despite the attachment of an inventive arrangement on a rotor of a gas turbine to allow a compact design of the rotor or the gas turbine.
  • At least one longitudinal edge of the web arranged on the side of the web remote from the blade root is preferably provided with a chamfer.
  • the chamfer can be formed by a mechanical reworking of the web formed on the blade.
  • both are provided on the side remote from the blade root of the web arranged longitudinal edges of the web, each with a chamfer. The formation of the chamfer or chamfers on the web allows for easier assembly of the arrangement, which is particularly difficult because the web is hardly or not visible during assembly of the arrangement.
  • the not provided with the recesses end of the securing bolt is preferably provided on a side facing the longitudinal bore with a at least over a part of the inner circumference of the longitudinal bore extending rounding.
  • the rounding can serve as a contact surface for a plastic deformation of the safety wire in order to bend a blade end remote from the safety pin end of the safety wire, preferably by 90 °.
  • This plastic deformation of the safety wire can be used to keep the safety pin permanently in its functional position. Without the rounding at the end of the securing bolt, damage to the securing wire could occur during bending of the safety wire and / or under mechanical stress during operation of a correspondingly formed gas turbine. This could in turn the durability of a corresponding fuse the functional position of the locking bolt are affected.
  • At least one free end of at least one recess is provided with a chamfer.
  • the chamfer can be formed by a mechanical reworking of the free end of the recess.
  • both free ends of each recess are each provided with a chamfer. The formation of the chamfer or chamfers on the recess or the recesses also allows a simpler installation of the arrangement, which is particularly difficult because the web is hardly or not visible during assembly of the arrangement.
  • the chamfers at the free ends of the recesses Due to the chamfers at the free ends of the recesses, it can come to a desired positive orientation of the securing bolt relative to the web at a contact between the safety pin or the chamfer formed on the chamfer and the web on which also chamfers may be formed attach the safety pin to the bridge as desired or to transfer the safety pin to its functional position.
  • the arrangement preferably comprises a sealing groove arranged on the blade side on a sealing wing formed on a platform of the blade, in which a radially outer edge section of the cover plate can be arranged.
  • a sealing groove arranged on the blade side on a sealing wing formed on a platform of the blade, in which a radially outer edge section of the cover plate can be arranged.
  • a cover plate can rotate about the safety pin to a certain extent in order to follow the tilting movements of the platforms to a certain extent.
  • the rotor assembly according to the invention for a rotor of a gas turbine comprises a rotor disk, a rotor blade arranged on the outer circumference of the rotor disk, a cover plate ring arranged on the outer circumference of the rotor disk and at least one arrangement according to one of the aforementioned embodiments or any combination thereof.
  • the rotor according to the invention for a gas turbine comprises at least one aforementioned rotor assembly.
  • the gas turbine according to the invention comprises an aforementioned rotor.
  • FIG. 1 shows a section of a side view of an embodiment of a blade 1 according to the invention, ie, a blade 1, which at the one in the FIGS. 7, 8 and 9 shown cover plate 2 facing side 3 of the blade root 4 of the blade 1 arranged web 5, which is arranged on the blade root 4, that the web 5 extends radially arranged at a not shown rotor disc rotor blade 1 with respect to the rotor.
  • the web 5 is arranged on a side facing the cover plate 2 side 3 of the blade root 4 recess 6, which is the Figures 2 and 9 can be better seen.
  • the web 5 is formed monolithically with the blade 1, wherein the two on the side facing away from the blade root 4 of the web 5 longitudinal edges of the web 5 are each provided with a chamfer 9. Above the recess 6, a sealing wing 7 of a platform 8 of the blade 1 is arranged.
  • FIG. 2 shows a section of a sectional view of in FIG. 1 shown blade 1 according to the in FIG. 1 shown arrow A.
  • On the sealing wing 7 of the platform 8 of the blade 1 is on the blade root side a sealing groove 10 is formed, in which a radially outer edge portion of the cover plate 2 can be arranged, as in FIG. 9 is shown.
  • the web 5 is flush with the rest of the cover plate 2 facing side 3 of the blade root 4 from, ie, that the height h of the web 5 corresponds to the depth of the recess 6.
  • FIG. 3 shows a perspective view of an embodiment of a securing bolt 11 of an inventive arrangement 12, as shown in FIG. 9 is shown.
  • the securing bolt 11 has a continuous longitudinal bore 13 and at one end two recesses 14 and 15, which are arranged diametrically opposite one another and are open towards this end.
  • the recesses 14 and 15 extend from this end of the securing bolt 11 parallel to the longitudinal axis L of the securing bolt 11 over part of the length of the securing bolt 11.
  • the width b A of the recesses and the diameter d L of the longitudinal bore 13 are equal to the width b S of Stegs 5.
  • the free ends of the recesses 14 and 15 are each provided with a chamfer 16.
  • the not provided with the recesses 14 and 15 end of the securing bolt 11 is provided on one of the longitudinal bore 13 facing side with a over the entire inner circumference of the longitudinal bore 13 extending rounding 17, which is better FIG. 4 can be removed.
  • FIG. 4 shows a longitudinal section through the in FIG. 3
  • the length l 1 of the shorter recess 14 is equal to the height h of the web 5.
  • the difference in length .DELTA.l, the width b A of the recesses 14 and 15, the width b S of the web 5 are equal to the diameter d of the longitudinal bore thirteenth
  • FIG. 5 shows an end view of the in the FIGS. 3 and 4 shown securing bolt 11 according to the arrow B from FIG. 4 ,
  • FIG. 6 shows a side view of an embodiment of a fuse wire 18 of the inventive arrangement 12.
  • the plastically deformable fuse wire 18 is L-shaped and has a shorter leg 19 and a longer leg 20.
  • the fuse wire 18 has a circular cross-section and is formed of metal.
  • the fuse wire 18 forms part of a securing device for securing the in FIG. 9 shown functional position of the securing bolt 11 on the cover plate 2 and the blade 1.
  • the length l 2 of the longer recess 15 is equal to the sum of the height h of the web 5 and the outer diameter d a of the fuse wire.
  • the diameter d L of the longitudinal bore 13, the difference in length ⁇ l, the width b A of the recesses 14 and 15 and the width b S of the web 5 are equal to the outer diameter d a of the safety wire 18th
  • FIG. 7 shows a section of a side view of an embodiment of a cover plate 2 according to the invention on the cover plate 2 is formed by a formed on the cover plate 2 thickening 21 guide portion 22 and formed by a arranged on the cover plate 2 through hole 23 guide opening 24, wherein the guide portion 22 completely surrounds the guide opening 24.
  • the securing device comprises a groove 26 arranged on the side 25 of the guide section 22 facing the blade root 4, which groove extends radially from the guide opening 24 over the guide section 22.
  • the width b N of the groove 26 is equal to the outer diameter d a of the safety wire 18.
  • the outer diameter d S of the securing bolt 11 is equal to the diameter d F of the guide opening 24th
  • FIG. 8 shows a section of a longitudinal section through the in FIG. 7 shown cover plate 2 according to the line CC FIG. 7 ,
  • FIG. 9 shows a section of a sectional view of an embodiment of an inventive arrangement 12 for securing the shown functional position of arranged on an outer periphery of a rotor of a rotor of a gas turbine cover plate 2 of the rotor relative to the arranged on the outer circumference of the rotor disc rotor blade 1 of the rotor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20130187993 2013-10-10 2013-10-10 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor Withdrawn EP2860351A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20130187993 EP2860351A1 (fr) 2013-10-10 2013-10-10 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor
CN201480055798.8A CN105637183B (zh) 2013-10-10 2014-09-04 用于固定布置在转子盘上的罩板的相对于布置在转子盘上的移动叶片的功能定位的装置
EP14759178.8A EP3019706B1 (fr) 2013-10-10 2014-09-04 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor
PCT/EP2014/068825 WO2015051956A1 (fr) 2013-10-10 2014-09-04 Ensemble servant à assurer une position fonctionnelle d'une plaque de recouvrement, disposée sur un disque de rotor, par rapport à une pale disposée sur le disque de rotor
US15/025,589 US10132173B2 (en) 2013-10-10 2014-09-04 Arrangement for securing a functional position of a shroud plate arranged on a rotor disc relative to a moving blade arranged on the rotor disc

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20130187993 EP2860351A1 (fr) 2013-10-10 2013-10-10 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor

Publications (1)

Publication Number Publication Date
EP2860351A1 true EP2860351A1 (fr) 2015-04-15

Family

ID=49356228

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20130187993 Withdrawn EP2860351A1 (fr) 2013-10-10 2013-10-10 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor
EP14759178.8A Active EP3019706B1 (fr) 2013-10-10 2014-09-04 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14759178.8A Active EP3019706B1 (fr) 2013-10-10 2014-09-04 Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor

Country Status (4)

Country Link
US (1) US10132173B2 (fr)
EP (2) EP2860351A1 (fr)
CN (1) CN105637183B (fr)
WO (1) WO2015051956A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564489A1 (fr) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
WO2010094539A1 (fr) 2009-02-17 2010-08-26 Siemens Aktiengesellschaft Segment de rotor pour le rotor d'une turbomachine, aube mobile pour une turbomachine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US600909A (en) * 1898-03-22 Heating device
BE551145A (fr) * 1955-09-26
US3070351A (en) * 1959-02-06 1962-12-25 Gen Motors Corp Blade retention
JP3442959B2 (ja) 1997-02-21 2003-09-02 三菱重工業株式会社 ガスタービン動翼の冷却媒体通路
JP2003314205A (ja) 2002-04-24 2003-11-06 Ishikawajima Harima Heavy Ind Co Ltd タービンディスクからのタービン翼抜け防止構造
US6749400B2 (en) 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
US8007230B2 (en) 2010-01-05 2011-08-30 General Electric Company Turbine seal plate assembly

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
WO2010094539A1 (fr) 2009-02-17 2010-08-26 Siemens Aktiengesellschaft Segment de rotor pour le rotor d'une turbomachine, aube mobile pour une turbomachine

Also Published As

Publication number Publication date
EP3019706A1 (fr) 2016-05-18
EP3019706B1 (fr) 2019-11-06
WO2015051956A1 (fr) 2015-04-16
CN105637183B (zh) 2017-11-21
US10132173B2 (en) 2018-11-20
CN105637183A (zh) 2016-06-01
US20160222799A1 (en) 2016-08-04

Similar Documents

Publication Publication Date Title
EP2873807A1 (fr) Plaque de recouvrement, aube mobile, disque de roue, boulon et turbine à gaz
EP3265713B1 (fr) Ensemble de raccord enfichable servant à raccorder des conduits
EP3999717B1 (fr) Élément intermédiaire pour une connexion aube-disque de rotor pour le rotor d'une turbomachine, rotor pour une turbomachine et turbomachine
WO1999030048A1 (fr) Cage de roulement a aiguilles et son procede de production
EP2907976A1 (fr) Procédé de montage d'une aube de turbine à gaz dans un logement supérieur d'un palier de rotor
WO1996005413A1 (fr) Element de compensation de jeu hydraulique pour commande de soupapes de moteurs a combustion interne
DE112011101698T5 (de) Turbolader
DE202016101760U1 (de) Getriebevorrichtung zur Anbringung an einer Antriebswelle
EP3061916A1 (fr) Agencement de disque de rotor et procédé de montage d'un agencement de disque de rotor
DE10350946B4 (de) Turbinendüsenhaltevorrichtung an der horizontalen Verbindungsfläche des Trägers
EP2133574A2 (fr) Grille de protection spatiale pour ventilateurs axiaux et procédé de fabrication de la grille de protection
EP1584793A2 (fr) Dispositif pour la fixation d'aubes de turbine
EP3019706B1 (fr) Agencement destiné à sécuriser une position fonctionnelle d'une plaque de couverture disposée au niveau d'un disque de rotor par rapport à une aube disposée au niveau du disque de rotor
DE112014005038T5 (de) Kernring mit eingeschnittenen oder eingestochenen Merkmalen
EP3025027B1 (fr) Aube de turbine et turbine à gaz
EP3983689B1 (fr) Support de palier à berceaux pivotants et procédé de fabrication d'un support de palier à berceaux pivotants
DE102016207155A1 (de) Stellantrieb
EP3170986B1 (fr) Groupe d'aubes avec un dispositif de retenue circonférentiel
EP3230559B1 (fr) Module final pour verrouiller une roue aubagée, organe de support d'aube, turbomachine et procédé d'insertion de module final associés
EP3313712B1 (fr) Articulation sphérique axiale
DE102013212486A1 (de) Leise laufende Hülsenkette mit abgesetzter Hülse
DE102015221765B3 (de) Zylinderanordnung mit einem Boden und Vorrichtung zur Herstellung einer Formschlussverbindung zwischen dem Boden und einem Zylinder
DE102011100221A1 (de) Abdeckeinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine
DE10140259C1 (de) Axialturbine
DE19757188A1 (de) Einrichtung zur Befestigung der Laufschaufeln einstufiger Axialturbinen

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: 20131010

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

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: 20151016