EP2569514B1 - Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication - Google Patents

Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication Download PDF

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Publication number
EP2569514B1
EP2569514B1 EP11723334.6A EP11723334A EP2569514B1 EP 2569514 B1 EP2569514 B1 EP 2569514B1 EP 11723334 A EP11723334 A EP 11723334A EP 2569514 B1 EP2569514 B1 EP 2569514B1
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EP
European Patent Office
Prior art keywords
blade
fastening assembly
groove
underside
retaining
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
EP11723334.6A
Other languages
German (de)
English (en)
Other versions
EP2569514A1 (fr
Inventor
Patrick Bullinger
Marco Link
Nicolas Savilius
Uwe Sieber
Hubertus Michael Wigger
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 EP11723334.6A priority Critical patent/EP2569514B1/fr
Publication of EP2569514A1 publication Critical patent/EP2569514A1/fr
Application granted granted Critical
Publication of EP2569514B1 publication Critical patent/EP2569514B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/94—Mounting on supporting structures or systems on a movable wheeled structure
    • 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
    • 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
    • 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
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • 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 fastening arrangement according to the preamble of claim 1. Furthermore, the invention relates to a method for producing such a fastening arrangement.
  • the present invention relates to the mechanical connection of stationary or rotating blades of the flow path of an axial-flow turbomachine. These are vanes which are fastened to the housing or to a corresponding guide blade carrier or to rotor blades which are arranged on the rotor of the turbomachine.
  • vanes of a blade ring are mounted in a circumferential groove.
  • rotating systems it is known that blades are inserted into a respectively associated, extending in the axial direction groove.
  • the object directed to the mounting arrangement is achieved by one which is designed according to the features of claim 1.
  • the object directed to the manufacturing method is achieved both with a method according to claim 11 and with a method according to claim 13.
  • the mounting arrangement according to the invention for blades of axially permeable turbomachinery comprises a blade carrier having a central axis and a concentric lateral surface, in which along the circumference distributed retaining grooves are provided with axial extension and blades whose blade roots are inserted into these retaining grooves, each retaining groove having a groove bottom which is opposite to an underside of the respective blade root, and in each case a resilient clamping element arranged between each groove base and the underside thereof, which prestresses on the relevant underside and on the relevant groove base, wherein in each case a groove is provided in the undersides of the blades, in which the relevant clamping element areal, ie rests along its longitudinal extent.
  • a suitable groove for guiding the clamping element is arranged in the groove base.
  • the invention is based on the finding that an improved contact pressure of the blade in the retaining groove can be achieved if at least on the blade root underside a groove is provided, in which the clamping element rests positively over its entire length.
  • a gutter is provided both in the blade root underside and in the groove bottom, these gutters can be produced particularly easily with the aid of the following methods.
  • the blades and the blade carrier are made including all retaining grooves.
  • the insertion of a blade takes place in the associated retaining groove.
  • the blade is temporarily fixed in the retaining groove.
  • the bore extends along the bottom groove bottom plane and cuts in half in the blade root and in the blade carrier.
  • the insertion of the clamping element takes place in the bore. It is preferably provided that the temporary fixation is released again before or after insertion of the tensioning element.
  • both channels can be produced simultaneously in a relatively simple manner and without unduly great expense. Since both channels are produced in only one drilling operation, it can be assumed that their position is very high in accuracy with respect to both channels, which results in a particularly reliable seating of the spring element in FIG causes the corresponding grooves. This has the consequence that with predetermined clamping forces the blade can be pressed in its retaining groove to the undercuts, in particular over the entire length of the undercuts.
  • a second method comprises the following steps: first, the blade carrier is produced, but without the associated retaining grooves. Subsequently, a drilling of the blade carrier, wherein the bores are respectively placed so that later in the production of one of the retaining grooves only a part of the surrounding hole in question material is removed. Subsequently, the retaining grooves are made in the blade carrier, wherein in each case during which only a part of the material surrounding the hole in question is removed, so that the remaining part of the material surrounding the hole in question forms the nutground worne groove. Subsequently, the insertion of blades takes place, in each case with the gutter already present on the underside and the insertion of the tensioning element into the space delimited by the opposing gutters.
  • This manufacturing method has the advantage that the channel arranged in the blade carrier can be prepared comparatively easily and without any special effort, in particular if the longitudinal directions of the channel and retaining groove are different.
  • both grooves extend parallel to the longitudinal extension of the retaining groove.
  • the grooves extend obliquely to the longitudinal extent of the retaining groove.
  • the latter variant has the particular advantage that due to the mutually inclined displacement direction of blades (along the retaining groove) and clamping element (along the channel) a positive connection between the blade root and groove by means of Clamping element is brought about, which also serves as axial securing against displacement of the blades along the retaining groove.
  • the clamping element is at the same time the Axialverschiebungs Klisfunktion.
  • the shearing forces acting on the clamping elements by the blades prevent the latter from being released from the channels.
  • the longitudinal extension of the retaining grooves is inclined relative to the central axis and the grooves extend parallel to the central axis.
  • the groove-base channel opens in at least one of the two end faces of the blade carrier, which adjoin the lateral surface. And / or the bottom channel opens into at least one of the two end faces of the blade root, which adjoin the bottom. Accordingly, from a lateral accessibility of the grooves for mounting the clamping element, which is preferably designed as a dowel pin, are assumed.
  • the end opening of one or more grooves is caulked.
  • the proposed mounting arrangement is applicable to both rotating and static systems.
  • the blade is formed as a blade with axial feet and the blade carrier as the rotor element, wherein at least a portion of the radially outer surface of the rotor element forms the respective lateral surface of the blade carrier with the corresponding retaining grooves.
  • each blade is formed as a vane with axial feet and the blade carrier as an annular vane support member, wherein at least a portion of the radially inner surface of the vane support forms the respective lateral surface of the blade carrier.
  • FIG. 1 shows a perspective view of a compressor blade formed as a blade 10.
  • the compressor blade includes a rudimentary only illustrated blade 12, to which a blade root 14 connects.
  • the blade root 14 has an outer contour which is dovetail-shaped, in order in an in FIG. 1 not shown blade carrier to be held positively.
  • the blade root 14 has an underside 16, in which a channel 18 is arranged.
  • the channel 18 will also be referred to below as the bottom channel 18.
  • the lower side groove 18 extends over the entire longitudinal extent of the Blade root 14 so that it ends at the end, dovetail-shaped contoured end surfaces of the blade root 14.
  • the channel 18 is in U-shape, thus groove-shaped with a semicircular basic contour and formed so deep that it can accommodate a trained as a clamping pin, not shown clamping element almost, but not completely. This makes it possible to fasten the blade 10 biased by means of the clamping pin in a holding groove, which has no groove-side groove.
  • FIG. 2 shows in perspective view a blade carrier 20 of a fastening arrangement 8.
  • a retaining groove 22 is provided, which has a contour corresponding to the blade root 14 of the blade 10.
  • the contour of the retaining groove 22 is not blade-footed but modified.
  • groove base 24 of the retaining groove 22 is a groove-side groove 26 is provided.
  • blade 10 differs from the in FIG. 1 illustrated blade 10 in that the channel 18 is not U-shaped, but is configured only approximately semicircular.
  • the openings of both channels 18, 26 face each other. Viewed in cross section, both channels 18, 26 form an approximately circular contour. They are also along their longitudinal extent always opposite each other and are thus suitable for receiving a clamping element 28, which is usually designed as a dowel pin.
  • clamping pin 28 arranged on the blade root 14 supporting flanks 30 are pressed against each forming an undercut flanks 32 of the retaining groove 22, whereby the blade 10 is intended radially held.
  • Both channels 18, 26 extend over the entire axial extent of the retaining groove 22, so that the clamping element 28 is used frontally ( FIG. 3 ). It should be noted that the clamping element 28 in FIG. 3 is shown only schematically by the cross section is shown rotated at 90 °.
  • the blade carrier 20 in FIG. 5 and the blade root 14 in FIG. 4 are schematically shown, the grooves 18, 26 extend transversely, ie obliquely to the longitudinal extent of the retaining groove 22.
  • the lower-side groove 18 now not frontally opens in the blade root 14, but the trailing edge side ( FIG. 4 ).
  • the groove-side groove 26 opens now not in the contour of the retaining groove 22, but outside of which as a bore opening. This is in FIG. 5 shown.
  • the mouth 34 of the nut brieflyen groove 26 outside the mouth 38 of the retaining groove 22.
  • the longitudinal displacement of the blade 10 along the retaining groove 22 is prevented in that the clamping element 28 on the one hand in a form-fitting manner in the bore or groove 26 and on the other hand also engages in the lower side groove 18 of the blade root 14. Due to the different displacement directions of the blade 10 - along the retaining groove 22 - and the clamping element 28 - along the grooves 18, 26 - the blade 10 is secured against displacement along the retaining groove 22 simultaneously with the insertion of the clamping element.
  • the invention provides a fastening arrangement 8 for blades 10 of axially permeable turbomachines, preferably compressors, comprising a blade carrier 20 with a lateral surface in which distributed along the circumference retaining grooves 22 are provided and in which Paddles 10 are used, wherein between each groove bottom 24 and the opposite bottom 16 of the respective blade root 14, a resilient clamping element 28 is provided, which is biased on the respective bottom 16 and the respective groove bottom 24, wherein both in the groove base 24 and in the Bottom 16 each have a groove 18, 26 is provided, in which the clamping element 28 abuts.

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

Claims (14)

  1. Agencement (8) de fixation d'aubes (10) de turbomachine axiale,
    comprenant
    un support (20) d'aube ayant un axe médian et une surface latérale, qui lui est concentrique et dans laquelle sont prévues des rainures (22) de maintien, réparties le long du pourtour, et des aubes (10) dont les emplantures (14) sont insérées dans les rainures (22) de maintien,
    dans lequel chaque rainure (22) de maintien a un fond (24) de rainure, qui est en face d'un côté (16) inférieur de l'emplanture (14) d'aube concernée et,
    entre chaque fond (24) de rainure et le côté (16) inférieur qui lui est opposé, est prévu respectivement un élément (28) de serrage, qui s'appuie avec précontrainte sur le côté (16) inférieur concerné et sur le fond (24) de rainure concernée,
    caractérisé en ce que
    l'élément (28) de serrage est constitué sous la forme d'un élément (28) de serrage à ressort et en ce que il est prévu, dans le côté (16) inférieur, une goulotte (18) dans laquelle l'élément (28) de serrage s'applique le long de son étendue longitudinale.
  2. Agencement (8) de fixation suivant la revendication 1, dans lequel il est prévu, dans le fond (24) de la rainure, une autre goulotte (26) qui est opposée à la goulotte (18) du côté inférieur.
  3. Agencement (8) de fixation suivant la revendication 2, dans lequel les deux goulottes (18, 26) s'étendent parallèlement à l'étendue longitudinale de la rainure (22) de maintien.
  4. Agencement (8) de fixation suivant la revendication 2, dans lequel les deux goulottes (18, 26) sont inclinées par rapport à la direction longitudinale de la rainure (22) de maintien.
  5. Agencement (8) de fixation suivant la revendication 4, dans lequel l'étendue longitudinale des rainures (22) de maintien est inclinée par rapport à l'axe médian et les goulottes (18, 26) s'étendent parallèlement à l'axe médian.
  6. Agencement (8) de fixation suivant l'une des revendications 2 à 5,
    dans lequel la goulotte (26), du côté du fond de la rainure, débouche dans au moins l'une des deux surfaces du côté frontal du support (20) d'aube, qui sont voisines de la surface latérale
    et/ou
    dans lequel la goulotte (18) du côté inférieur débouche dans au moins l'une des deux surfaces du côté frontal de l'emplanture (14) d'aube, qui est voisine du côté (16) inférieur.
  7. Agencement (8) de fixation suivant l'une des revendications 2 à 6,
    dans lequel deux goulottes (18, 26) opposées l'une à l'autre, paire par paire, forment un évidement sensiblement circulaire.
  8. Agencement (8) de fixation suivant l'une des revendications précédentes,
    dans lequel l'élément (28) de serrage est constitué sous la forme d'une broche de serrage, dont la longueur axiale est à peu près égale à la longueur de la rainure de la goulotte (18, 26).
  9. Agencement (8) de fixation suivant l'une des revendications précédentes,
    dans lequel l'élément (28) de serrage est maté pour s'assurer vis-à-vis d'une perte.
  10. Agencement (8) de fixation suivant l'une des revendications précédentes,
    dans lequel chaque aube (10) est constituée en aube mobile et le support (20) d'aube est constitué en élément rotorique,
    dans lequel au moins une partie de la surface latérale extérieure radialement de l'élément rotorique forme la surface latérale concernée du support (20) d'aube.
  11. Agencement (8) de fixation suivant l'une des revendications 1 à 9,
    dans lequel chaque aube (10) est constituée en aube directrice et le support (20) d'aube est constitué sous la forme d'un support annulaire d'aube directrice,
    dans lequel au moins une partie de la surface latérale intérieure radialement du support d'aube directrice forme la surface latérale concernée du support (20) d'aube.
  12. Procédé de fabrication d'un agencement (8) de fixation suivant l'une des revendications 2 à 11,
    comprenant les stades successifs
    • fabrication des aubes (10) et du support (20) d'aube, ensemble avec toute les rainures (22) de maintien,
    • insertion d'une aube (10) dans l'une des rainures (22) de maintien,
    • immobilisation temporaire de l'aube (10) dans la rainure (22) de maintien,
    • fabrication par paire de deux goulottes (18, 26) opposées l'une à l'autre par une opération de perçage, le long d'un plan côté inférieur - fond de rainure et
    • insertion de l'élément (28) de serrage dans le perçage.
  13. Procédé suivant la revendication 12,
    dans lequel on met fin à l'immobilisation temporaire, avant ou après l'insertion de l'élément (28) de serrage.
  14. Procédé de fabrication d'un agencement (8) de fixation suivant l'une des revendications 2 à 11,
    comprenant les stades successifs
    • fabrication du support (20) d'aube sans rainure (22) de maintien,
    • perçage du support (20) d'aube, les perçages étant placés respectivement de manière à ce que, lors de la fabrication de l'une des rainures (22) de maintien, seulement une partie du matériau entourant le perçage soit éliminée,
    • fabrication des rainures (22) de maintien, pendant laquelle respectivement seule une partie du matériau entourant le perçage concerné est éliminée, de sorte que la partie restante du matériau entourant le perçage concerné forme la goulotte (26) du côté du fond de la rainure,
    • insertion d'aubes (10) ayant respectivement une goulotte (18) déjà présente du côté du fond et
    • insertion de l'élément (28) de serrage dans l'espace délimité par des goulottes (18, 26) opposées l'une à l'autre.
EP11723334.6A 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication Not-in-force EP2569514B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11723334.6A EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10005079A EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
PCT/EP2011/057628 WO2011141514A1 (fr) 2010-05-14 2011-05-11 Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement
EP11723334.6A EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Publications (2)

Publication Number Publication Date
EP2569514A1 EP2569514A1 (fr) 2013-03-20
EP2569514B1 true EP2569514B1 (fr) 2014-04-02

Family

ID=43017149

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10005079A Withdrawn EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP11723334.6A Not-in-force EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10005079A Withdrawn EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Country Status (6)

Country Link
US (1) US20130101422A1 (fr)
EP (2) EP2386721A1 (fr)
JP (1) JP5596223B2 (fr)
CN (1) CN102906375A (fr)
RU (1) RU2012154199A (fr)
WO (1) WO2011141514A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2025021442A1 (fr) 2023-07-27 2025-01-30 Siemens Energy Global GmbH & Co. KG Pale à geometrie de pied simplifiee

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DE102012200891A1 (de) * 2012-01-23 2013-07-25 Mtu Aero Engines Gmbh System zur Vorgabe einer Einbauposition von Laufschaufeln, Sicherungselement, Laufschaufel, Turbomaschine sowie Verfahren
FR2990462B1 (fr) * 2012-05-14 2014-05-30 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine
US20130333173A1 (en) * 2012-06-15 2013-12-19 Mitsubishi Heavy Industries, Ltd. Blade root spring insertion jig and insertion method of blade root spring
CA2880516C (fr) * 2012-08-01 2017-08-08 Derek Thomas Dreischarf Jointure de boucle pour un carenage divise d'un moteur a turbine a gaz
US20140072419A1 (en) * 2012-09-13 2014-03-13 Manish Joshi Rotary machines and methods of assembling
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CN102906375A (zh) 2013-01-30
RU2012154199A (ru) 2014-06-20
JP2013526667A (ja) 2013-06-24
EP2386721A1 (fr) 2011-11-16
WO2011141514A1 (fr) 2011-11-17
EP2569514A1 (fr) 2013-03-20
US20130101422A1 (en) 2013-04-25
JP5596223B2 (ja) 2014-09-24

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