EP2488725B1 - Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque - Google Patents

Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque Download PDF

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Publication number
EP2488725B1
EP2488725B1 EP10785099.2A EP10785099A EP2488725B1 EP 2488725 B1 EP2488725 B1 EP 2488725B1 EP 10785099 A EP10785099 A EP 10785099A EP 2488725 B1 EP2488725 B1 EP 2488725B1
Authority
EP
European Patent Office
Prior art keywords
turbine wheel
ring
hooks
tab
blade
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.)
Active
Application number
EP10785099.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2488725A1 (fr
Inventor
Damien Chauveau
Jean-Luc Sahores
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.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca SA
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 Turbomeca SA filed Critical Turbomeca SA
Priority to PL10785099T priority Critical patent/PL2488725T3/pl
Publication of EP2488725A1 publication Critical patent/EP2488725A1/fr
Application granted granted Critical
Publication of EP2488725B1 publication Critical patent/EP2488725B1/fr
Active 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
    • 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
    • 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
    • F01D5/326—Locking of axial insertion type blades by other 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
    • 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
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates generally to paddle wheels in gas turbines and more particularly to the axial retention of said blades relative to the axis of the wheel.
  • the field of application of the invention is in particular that of aircraft gas turbines as well as that of industrial gas turbines.
  • a conventional turbine wheel has an axis of rotation and comprises a disc having a periphery and a lateral face, a plurality of blades mounted on the disc, each of the blades having a blade root and a first axially projecting hook, said first hook being oriented radially and defining a first groove which opens radially towards the axis of rotation of the turbine wheel, the disc comprising a series of second hooks axially projecting from its lateral face on the same side as the first hooks, each second hook being oriented radially and defining a second groove which opens radially towards the axis of rotation of the turbine wheel, an axial retaining ring comprising at least one stopper and intended to be arranged in the first grooves and in the second grooves to axially retain the blades relative to the disk.
  • a cleat of the ring is locked in rotation between different parts of the turbine wheel in order to secure the assembly of the ring and the retention of the blades on the disk.
  • the object of the invention is to provide an alternative to known turbine wheel mounting structures.
  • the cleat is intended to be disposed between two adjacent blade feet so as to limit the azimuthal displacements of the rod.
  • foot means the entire blade disposed at the base of the blade for mounting the latter on the disk. It will be noted that subsequently the term “wheel” and “turbine wheel” will be used interchangeably to designate the same object. It is therefore understood that in mounted position, the azimuth displacement of the cleat is restricted by two adjacent blade feet. To do this the cleat can abut against one or the other of the two feet of blade. Therefore the azimuthal movement of the ring is limited.
  • the cleat is disposed in a space that extends between the two adjacent blade legs so that no particular machining is necessary, especially to provide space for housing the cleat. It is therefore possible to mount on the wheel a set of blades having identical feet. In addition, the blades can be all identical, mounting the wheel is facilitated. Indeed, the operator does not pay particular attention to the placement of a blade having a specific foot vis-à-vis the cleat.
  • the azimuthal movement of the rod is at most equal to the azimuthal length of the available space between two adjacent feet minus the azimuthal length of the cleat.
  • the cleat extends over most of the azimuthal length, it is useful to provide a non-zero maximum azimuth displacement of the rod, in particular to facilitate assembly and to compensate for thermal expansion differentials.
  • the first grooves are defined between the first hooks and the blade roots while the second grooves are defined between the second hooks and the disc. The ring moves azimutally in the first and second grooves.
  • the arrangement of the cleat between two blade roots advantageously makes it possible to dispense with a particular machining of said cleat, in particular to allow its insertion between the two blade roots.
  • this arrangement between two blade roots makes it possible to place the cleat between any pair of blade roots.
  • the turbine wheel according to the present invention is not limited to a single mounting position of the cleat, and therefore the rod, vis-à-vis the wheel of turbine.
  • the cleat is axially projecting from an axial face of the ring.
  • axial face of the ring means a face of the ring which is perpendicular to the axis of rotation of the turbine.
  • an axial face of the ring is a face substantially parallel to the lateral face of the disc.
  • the stopper projects in an axial direction opposite to the lateral face of the disc.
  • the cleat is disposed on an inner annular portion of the ring.
  • the inner annular portion of the ring is determined to be a portion of the bounded ring. by the inner peripheral edge and the intermediate line of the ring, while the outer annular portion of the ring is defined as being a portion of the ring delimited by the outer peripheral edge and the intermediate line of the ring. It is therefore understood that the cleat extends radially on an axial face of the ring, between the inner peripheral edge and the intermediate line of the ring.
  • the cleat is intended to be disposed between the first hooks of two feet of adjacent blade.
  • the cleat is able to cooperate with said first hooks of the blade roots in order to limit the azimuthal movement of the ring. It is therefore clear that the azimuthal space in which the cleat extends is delimited azimuthally by the first hooks. Thus, the first hooks have a stop zone for the cleat.
  • the cleat is intended to be arranged in line with one of the second hooks.
  • one of the second hooks is disposed in the azimuthal space available between two adjacent blade feet.
  • This second hook and the cleat are arranged substantially on the same wheel radius.
  • the second hook is radially further from the axis of rotation of the turbine wheel than the cleat.
  • the second hook is oriented towards the cleat.
  • the minimum distance between the outer peripheral edge of the ring and the stopper is greater than the depth of one of the second grooves.
  • the cleat is in line with a second hook, it is ensured that the outer edge of the ring is adapted to be in contact with the bottom of the second groove, for example under the effect of centrifugal forces.
  • the second hook is likely to cooperate with the second hook. Therefore radial mechanical stresses on the cleat are avoided which are not used to limit the azimuthal movement of the ring. This improves the life of the rod.
  • it also limits the mechanical bending stresses in the second hook disposed above the cleat, avoiding a tab contact / second hook. Therefore, the cooperation of the ring is identical with each of the second grooves of the disk, regardless of the presence of the cleat.
  • the first hook of each of the blades is radially projecting from the foot of said blades.
  • This first hook structure makes it easy to manufacture first hooks whose first grooves are arranged in the azimuthal continuity of the second grooves of the disc. Thus, when the blades are mounted on the disc, the first hooks axially protrude from the plane defined by the side face of the disc.
  • the foot of each blade is engaged in a housing opening at the periphery of the disk, the housing being separated by teeth, each second hook projecting from one of the teeth.
  • the circumferential groove receiving the ring consists of an alternating succession of first and second grooves. It should be noted that the circumferential groove is not necessarily continuous and may have gaps between the first grooves and the second grooves. Such a groove structure allows to evenly distribute the blade retaining forces over the entire periphery of the disk. This also makes it possible to better maintain the ring and thus to avoid dynamic effects harmful to the structure such as vibrations.
  • the cleat has contact faces adapted to make a plane contact with bearing faces of the two blade roots which limit the azimuthal movement of the ring.
  • the ring has a slot diametrically opposite the cleat.
  • the slot of the ring facilitates the mounting of the latter in the first and second grooves.
  • the position of the slot diametrically opposite the cleat improves the functional reliability of the ring. Indeed, if a rupture of the latter should occur, this break would most likely be located at the cleat. The broken ridge would then form two half-rods of substantially equivalent lengths that could not disengage from the first and second hooks.
  • the presence of a single cleat disposed opposite the slot makes it possible to concentrate the mechanical stresses undergone by the rod in the vicinity of said cleat opposite the slot and, consequently, to improve the functional reliability. of the rush.
  • the ring is arranged in the first and second grooves by varying the radial flexibility of the ring and arranging from the start the cleat between two blade roots.
  • the ring has the general shape of a ring having an axis, the center of gravity of said ring being located on said axis.
  • a balanced ring has the advantage of not influencing the balance of the rotating assembly constituted by the disk and the blades. Thus, it is not necessary to provide a particular machining on the turbine wheel to compensate for an imbalance that would be due to a nonuniform distribution of masses. Therefore, it is possible to mount the rod in all possible azimuthal positions without disturbing the homogeneous azimuth distribution of the masses, so that the assembly of the turbine wheel is facilitated.
  • the present invention also relates to a turbomachine comprising a turbine wheel according to the invention.
  • the figure 1 represents a portion of a turbine wheel 10 with a rotation axis X.
  • the turbine wheel 10 comprises a disk 12 and a plurality of blades 14.
  • the disk 12 has at its periphery a plurality of teeth 16 spaced apart by housings 18.
  • Each blade 14 of the turbine wheel 10 is engaged in a housing 18 at its foot 20.
  • Each foot 20 of blade 14 has a first hook 22 projecting axially (along the X axis).
  • the first hook 22 is oriented radially and forms a first groove 24 which opens radially towards the axis of rotation X of the wheel 10.
  • radial orientation is meant “oriented according to a radius of the "turbine wheel” while “axial orientation” means “oriented along the axis of rotation of the turbine”.
  • Each tooth 16 of the disk 12 has a second hook 26 which projects axially (along the X axis).
  • the second hook 26 is oriented radially and defines a second groove 28.
  • the first and second hooks 22 and 26 extend axially from the plane defined by the lateral face 12a of the disk 12, on the same side.
  • the first grooves 24 and the second grooves 28 are azimutally aligned. According to the azimuthal direction, the first hooks 22 alternate with the second hooks 26.
  • azimuthal direction is meant “oriented along the circumference of the turbine wheel”.
  • the first hook 22 is located at the base of the attachment of the blade and the second hooks 26 at the base of the teeth 16.
  • the first hook 22 could be placed on another part of the foot, for example under the platform of the blade 14.
  • the second hooks 26 would then be placed at the top of the teeth 16.
  • the radial position of the hooks can be adapted.
  • a rod 30 is disposed in the first grooves 24 and in the second grooves 28.
  • This ring 30 has an annular shape about an axis which coincides with the axis of rotation X of the turbine.
  • the ring 30 has a single catch 32 disposed on an axial face of the ring 30, opposite the lateral face 12a of the disc 12.
  • the catch 32 is disposed between two adjacent feet 20 of two adjacent blades 14.
  • the azimuthal ends 32a cleat 32 are able to abut against the feet 20 which surround it, and more particularly with the first hooks 22, to limit the azimuthal movement of the rod 30 in the first and second grooves 24 and 28.
  • the cleat 32 is also placed in line with a second hook 26. Whatever the mechanical conditions experienced by the rod 30, the cleat 32 does not come into contact with the second hook 26, neither radially nor azimuthally. Thus, the first hooks 22 are radially longer than the second hooks 26 so that the first hooks 22 are able to cooperate with the catch 32 while the second hooks 26 leave the catch 32 (and therefore the rod 30) free of movement. azimuthal. Consequently, the first grooves 24 defined by the first hooks 22 are deeper than the second grooves 28 defined by the second hooks 26.
  • the rod 30 has an outer annular portion 30a on which the tab 32 does not extend.
  • the cleat 32 is disposed on an inner annular portion 30b of the ring 30.
  • the inner annular portion 30b is delimited and separated from the outer annular portion 30a by the intermediate line 30c of the axial face supporting the cleat 32.
  • This intermediate line 30c is a brand machining a chamfer 31a made at the inner peripheral edge 30d on the axial face supporting the latch 32 (cf. fig.2 and 4 ).
  • the figure 2 represents the engagement of the rod 30 in a first groove 24, seen according to the sectional plane II of the figure 1 .
  • the figure 3 represents the engagement of the rod 30 in a second groove 28, seen according to the sectional plane III of the figure 1 .
  • the depth of the second grooves 28 is less than the distance between the outer peripheral edge 30e of the ring 30 and the catch 32 so that on the figure 3 , the outer peripheral edge 30e of the ring 30 cooperates with the bottom 28c of the second groove 28 while the catch 32 is radially distant from the edge 26a of the second hook 26 at least one set j1.
  • the clearance j1 is greater than the radial deformations of the rod 30 at the cleat 32 when the turbine wheel 10 operates.
  • the bottom 24c of the first grooves 24 is radially further from the axis of rotation X of the turbine wheel 10 than the bottom 28c of the second grooves 28 so that the outer peripheral edge 30e of the rod 30 remains at a minimum.
  • the clearance j2 is greater than the radial deformation of the ring 30 between two first and second hooks 22 and 26.
  • the ring 30 is held radially only by the second hooks 26 while it cooperates in the axial direction with the first and second hooks 22 and 26.
  • the ring 30 also cooperates with the lateral face 12a of the disc 12
  • the rod 30 cooperates radially only with the bottom 28c of the second grooves 28 while it co-operates axially with the lateral faces 24a and 24b of the first grooves 24, with the lateral faces 28a and 28b of the second gorgs. 28, as well as with the lateral face 12a of the disk 12.
  • the rod 30 cooperates radially only with the second hooks 26. This has the advantage of limiting the contact wear experienced by the first hooks 22, particularly at The bottom of the first grooves 24. This assembly thus limits the risk of rupture of the first hooks 22 of blade 14.
  • the ring 30 has chamfers 31b and 31c on its axial faces to facilitate its insertion into the first and second grooves 24 and 28.
  • the width of the bevel 31b made on the axial face supporting cleat 32 is less important than the width of the chamfer 31c made on the axial face opposite the lateral face 12a of the disc 12.
  • width of the chamfer means the dimension of the chamfer which extends radially on the chamfered portion of the ring.
  • the figure 4 represents the rod 30 in perspective.
  • the ring 30 has a slot 34 diametrically opposed to the stop 32.
  • the slot 34 is beveled, that is to say that it extends obliquely with respect to a radius of the ring 30.
  • This beveled slot 34 allows easily bend the ring 30 radially in order to insert it into the first and second grooves 24 and 28.
  • the beveled shape of the slot 34 makes it possible to avoid an interaction between the ends of the ring 30 delimiting the edges of the slot 34 which block and limit the elastic deformation of the ring 30 during assembly.
  • the rod 30 is maintained in the first and second grooves 24 and 28 by its natural elasticity while when the turbine wheel 10 is in operation the ring 30 is further maintained in the first and second grooves 24 and 28 by the centrifugal forces.
  • the slot 34 is disposed in a first or second groove 24 or 28 so that a first or second hook 22 or 26 limits and / or blocks the axial movements of the ends of the ring 30 delimiting the slot 34.
  • the slot is disposed in one of the second grooves 28, under one of the second hooks 26.
  • the azimuthal length the cleat 32 is such that the maximum authorized azimuth movements of the rod leave the slot 34 engaged in a first or second groove 24 or 28.
  • the azimuthal length of the cleat 32 is such that the slot 34 does not disengage a first or second groove 24 or 28, even when the stop 32 abuts on one of the feet 20 which surround it.
  • the radial thickness E of the ring 30 varies along the perimeter of the ring 30.
  • the radial thickness E of the ring 30 varies. continuously and progressively between the minimum radial thickness Emin at the cleat 32 and the maximum radial thickness Emax at the slot 34.
  • the radial thickness variation E is essentially effected at the inner annular portion 30b of the ring 30.
  • the center of gravity G of the ring 30 is located on the axis of the ring 30, preferably at the intersection of the median plane of the ring 30.
  • the azimuth balance of the ring can be achieved by adjusting the shape of the chamfers 31a, 31b and 31c.
  • the combination of both adjustments (chamfer and radial thickness) is also feasible.
  • the cleat 32 does not have a preferred azimuthal position within the wheel 10, so-called third-party operations, of choosing an azimuthal position of the cleat 32 to improve the overall balance of the wheel 10, are possible .
  • the figure 5 represents a helicopter turbine engine 100 equipped with the turbine wheel 10.
  • a second turbine wheel 110 may advantageously be made according to the invention, but not necessarily.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10785099.2A 2009-10-13 2010-10-12 Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque Active EP2488725B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL10785099T PL2488725T3 (pl) 2009-10-13 2010-10-12 Wirnik turbiny wyposażony w pierścień do osiowego ustalania, ryglujący łopaty względem tarczy

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0957150A FR2951224B1 (fr) 2009-10-13 2009-10-13 Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
PCT/FR2010/052151 WO2011045520A1 (fr) 2009-10-13 2010-10-12 Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque

Publications (2)

Publication Number Publication Date
EP2488725A1 EP2488725A1 (fr) 2012-08-22
EP2488725B1 true EP2488725B1 (fr) 2013-07-24

Family

ID=42270090

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10785099.2A Active EP2488725B1 (fr) 2009-10-13 2010-10-12 Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque

Country Status (12)

Country Link
US (1) US9163520B2 (ru)
EP (1) EP2488725B1 (ru)
JP (1) JP5547292B2 (ru)
KR (1) KR101711374B1 (ru)
CN (1) CN102575524B (ru)
CA (1) CA2776854C (ru)
ES (1) ES2426676T3 (ru)
FR (1) FR2951224B1 (ru)
IN (1) IN2012DN03202A (ru)
PL (1) PL2488725T3 (ru)
RU (1) RU2550226C2 (ru)
WO (1) WO2011045520A1 (ru)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008008887A1 (de) * 2008-02-13 2009-08-27 Man Turbo Ag Mehrteiliger beschaufelter Rotor für eine Strömungsmaschine
GB201404362D0 (en) * 2014-03-12 2014-04-23 Rolls Royce Plc Bladed rotor
FR3029962B1 (fr) * 2014-12-11 2019-08-23 Safran Aircraft Engines Blocage axial des aubes dans une roue de turbomachine
EP3073052B1 (en) 2015-02-17 2018-01-24 Rolls-Royce Corporation Fan assembly
CN105221478B (zh) * 2015-09-17 2018-11-13 中国航空工业集团公司沈阳发动机设计研究所 一种压气机转子叶片止动环及具有其的叶轮
FR3049643A1 (fr) * 2016-03-31 2017-10-06 Turbomeca Roue a pales rapportees et turbomachine equipee d'une telle roue
US10724384B2 (en) * 2016-09-01 2020-07-28 Raytheon Technologies Corporation Intermittent tab configuration for retaining ring retention
US10400614B2 (en) * 2016-11-18 2019-09-03 General Electric Company Turbomachine bucket with radial support, shim and related turbomachine rotor
US20180179952A1 (en) * 2016-12-23 2018-06-28 General Electric Company Rotating detonation engine and method of operating same
US10865646B2 (en) 2017-05-04 2020-12-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10774678B2 (en) 2017-05-04 2020-09-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10968744B2 (en) * 2017-05-04 2021-04-06 Rolls-Royce Corporation Turbine rotor assembly having a retaining collar for a bayonet mount
US10765160B2 (en) * 2017-07-18 2020-09-08 Lucy Page Skin protecting garment
EP3581765A1 (de) * 2018-06-11 2019-12-18 Siemens Aktiengesellschaft Rotor mit an der rotorscheibe axial verriegelten laufschaufeln
US20200131916A1 (en) * 2018-10-31 2020-04-30 United Technologies Corporation Turbine blade assembly
GB201819412D0 (en) * 2018-11-29 2019-01-16 Rolls Royce Plc Geared turbofan engine
USD981316S1 (en) * 2019-10-31 2023-03-21 Otr Wheel Engineering, Inc. Wheel lock ring assembly
JP7213835B2 (ja) 2020-02-10 2023-01-27 三菱重工業株式会社 タービンホイール
FR3123681B1 (fr) 2021-06-08 2023-11-10 Safran Helicopter Engines Roue de rotor pour une turbomachine d’aéronef
FR3123682A1 (fr) 2021-06-08 2022-12-09 Safran Helicopter Engines Roue de rotor pour une turbomachine d’aéronef

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB894704A (en) * 1960-03-30 1962-04-26 Gen Electric Improvements in reusable locking means for turbine or compressor rotor assemblies
US3888601A (en) 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
FR2695433B1 (fr) * 1992-09-09 1994-10-21 Snecma Joint annulaire d'étanchéité disposé à une extrémité axiale d'un rotor et recouvrant des brochages d'aubes.
FR2728299B1 (fr) * 1994-12-14 1997-01-24 Snecma Dispositif de fixation axiale d'aubes de rotor de turboreacteur
FR2729709A1 (fr) * 1995-01-25 1996-07-26 Snecma Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
JP4042006B2 (ja) * 1998-02-04 2008-02-06 株式会社Ｉｈｉ 動翼の抜止構造
US6234756B1 (en) * 1998-10-26 2001-05-22 Allison Advanced Development Company Segmented ring blade retainer
GB0302116D0 (en) 2003-01-30 2003-03-05 Rolls Royce Plc A rotor
DE10348198A1 (de) * 2003-10-16 2005-05-12 Rolls Royce Deutschland Schaufelrückhaltevorrichtung
WO2006014691A1 (en) 2004-07-21 2006-02-09 Underground Systems, Inc. Dynamic line rating system with real-time tracking of conductor creep to establish the maximum allowable conductor loading as limited by clearance
FR2890104A1 (fr) * 2005-08-31 2007-03-02 Snecma Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et moteur d'aeronef les comportant
RU2330163C1 (ru) * 2006-11-01 2008-07-27 Открытое акционерное общество "Силовые машины-ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (ОАО "Силовые машины") Рабочее колесо газовой турбины

Also Published As

Publication number Publication date
RU2550226C2 (ru) 2015-05-10
ES2426676T3 (es) 2013-10-24
CA2776854C (fr) 2017-02-28
CN102575524B (zh) 2014-12-10
CA2776854A1 (fr) 2011-04-21
RU2012119602A (ru) 2013-11-20
US9163520B2 (en) 2015-10-20
PL2488725T3 (pl) 2013-11-29
WO2011045520A1 (fr) 2011-04-21
KR101711374B1 (ko) 2017-03-02
US20120201681A1 (en) 2012-08-09
JP2013507572A (ja) 2013-03-04
EP2488725A1 (fr) 2012-08-22
IN2012DN03202A (ru) 2015-10-23
FR2951224B1 (fr) 2011-12-09
KR20120092125A (ko) 2012-08-20
FR2951224A1 (fr) 2011-04-15
CN102575524A (zh) 2012-07-11
JP5547292B2 (ja) 2014-07-09

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