EP1746250A1 - Vibrationsdämpfungselemente für einen axialen Haltering von Bläserschaufeln einer Turbomaschine - Google Patents

Vibrationsdämpfungselemente für einen axialen Haltering von Bläserschaufeln einer Turbomaschine Download PDF

Info

Publication number
EP1746250A1
EP1746250A1 EP06117009A EP06117009A EP1746250A1 EP 1746250 A1 EP1746250 A1 EP 1746250A1 EP 06117009 A EP06117009 A EP 06117009A EP 06117009 A EP06117009 A EP 06117009A EP 1746250 A1 EP1746250 A1 EP 1746250A1
Authority
EP
European Patent Office
Prior art keywords
flange
ring
retaining ring
disk
fan blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06117009A
Other languages
English (en)
French (fr)
Other versions
EP1746250B1 (de
Inventor
Jean-Bernard Forgue
Jack-Pierre Lauvergnat
Henry Loiseau
Didier Monnet
Thierry Nitre
Patrick Reghezza
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1746250A1 publication Critical patent/EP1746250A1/de
Application granted granted Critical
Publication of EP1746250B1 publication Critical patent/EP1746250B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/32—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
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/431—Rubber

Definitions

  • the present invention relates to the general field of assembly of the fan blades on a rotating disc of a turbomachine. It relates more particularly to a device for damping the vibrations undergone by the axial retention ring of the fan blades.
  • the fan of a turbomachine typically consists of a plurality of blades mounted on a rotating disc via their foot which is fitted into recesses of the disc.
  • a ring is also disposed around an annular flange which extends axially on the upstream side of the rotating disk. Such a ring is held axially against the flange by means of crenellations formed on the entire circumference of the latter.
  • the ring is also mounted in axial abutment against the blade root to ensure axial retention of the latter.
  • this type of fan blade assembly poses many problems.
  • wear has been noted on the axial retention ring and the rotating disk. These wearings are mainly caused by the vibrations experienced by the axial retention ring during the rotation of the disc.
  • the rotation of the disk causes low deflections of the axial retention ring which cause wear on the crest of the slots of the annular flange for holding the ring on the disk.
  • the axial retention ring tends to move tangentially around the flange of the disc.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing a device for damping the vibrations undergone by the axial retention ring of the fan blades.
  • a device for damping the vibrations of an axial retaining ring of the fan blades of a turbomachine said fan blades being intended to be mounted by their feet on a rotating disc comprising an annular flange. extending axially and provided with a plurality of radial slots for engaging a plurality of complementary radial slots of a retention ring for mounting around the disk flange, said device being characterized in that it consists of a stop element made of elastomeric material intended to be housed axially between two adjacent crenellations of the flange and two adjacent adjacent crenellations of the retention ring and radially between the flange of the rotating disc and the retention ring. said stop member having contact surfaces for contacting said adjacent slots, the ring of rim tention and the flange of the rotary disk.
  • the device according to the invention makes it possible to modify the natural modes of vibration of the retention ring.
  • this device consisting of an elastomeric material element, the surfaces of the latter which are in contact with the retaining ring and the flange of the disc tend to be pressed by centrifugal effect against the retention ring and the bridle.
  • the vibrations undergone by the retaining ring are damped and any risk of wear is eliminated.
  • the use of such a damping device also makes it possible to ensure tangential locking of the retention ring around the flange of the disc.
  • the stop element of the damping device may be substantially parallelepipedal. It may also have a geometric shape to ensure its keying when mounted on the disc.
  • the elastomeric material of the abutment element has a hardness of between 50 and 90 shore.
  • This elastomeric material is preferably a silicone, a fluorosilicone or a fluorocarbon.
  • the invention also relates to a ring for axial retention of the fan blades of a turbomachine comprising at least one damping device of the aforementioned vibrations.
  • the invention also relates to a turbomachine rotating disc for mounting fan blades, comprising an axially extending annular flange and provided with a plurality of radial slots intended to come into contact with a plurality of complementary radial slots. of an axial retaining ring of the fan blades intended to be mounted around the flange of the disk, the disk further comprises at least two damping devices as defined above.
  • the subject of the invention is a turbomachine comprising at least one rotating disk as defined above.
  • FIGS 1 and 2 partially show a disk 10 of turbomachine blower. This disc 10 is able to rotate about the longitudinal axis XX of the turbomachine.
  • the rotating disk 10 has a plurality of recesses 12 regularly distributed over its entire outer circumference, each recess being intended to receive the foot 14 of a fan blade 16 (only one blade is partially shown in FIG. 1).
  • the foot 14 of each blade 16 has a shape of dovetail which is axially slip into the recesses 12 provided for this purpose.
  • the rotating disc 10 also has an annular flange 18 which extends axially upstream. At its end opposite the disk, this flange 18 is provided with a plurality of outer teeth (or teeth) 20 which extend radially outwardly of the disk and which are regularly distributed over the entire circumference of the disk.
  • the number of outer slots 20 of the flange 18 is identical to the number of recesses 12 of the disc intended to receive the fan blades 16. Moreover, the outer slots 20 are substantially aligned (in the axial direction) with these recesses 12.
  • the flange 18 is also provided with an annular flange 22 which extends radially towards the inside of the disk (that is to say towards the axis XX of rotation of the latter). .
  • This flange 22 has orifices 24 distributed over its entire circumference. It is intended to receive an annular flange 26 held against it by means of screws 28 which are housed in the orifices 24. The role of such a flange is to block the tangential displacement of the ring and to fill other functions within the turbomachine fan (in particular holding the inter-blade platforms).
  • An axial retaining ring 30 of the vanes 16 is intended to be mounted around the flange 18 of the disc 10.
  • This retaining ring 30 has a plurality of inner slots (or teeth) 32 extending radially inwardly of the disc which are intended to come into axial contact with the outer slots 20 of the flange 18 when the ring is mounted around the latter.
  • the number of slots of the flange and the retention ring is therefore identical.
  • the retaining ring 30 is provided with outer teeth (or teeth) 34 which extend radially outwardly of the disc and which are aligned radially with its inner slots 32.
  • outer teeth (or teeth) 34 which extend radially outwardly of the disc and which are aligned radially with its inner slots 32.
  • the retaining ring 30 is held axially on the flange 18 of the disk by the contact between its inner slots 32 and the outer slots 20 of the flange.
  • the retention ring can thus ensure an axial retention of the blade roots 14 in their respective recesses 12.
  • the mounting of the retention ring 30 on the flange 18 of the disc is carried out in the following manner: the ring is centered on the longitudinal axis XX of the turbomachine with its inner slots 32 offset axially with respect to the outer slots 20 of the flange 18 of the disc.
  • the ring is brought around the flange, each of its inner crenellations 32 inserted between two adjacent outer crenellations 20 of the flange.
  • the ring is then pivoted about the longitudinal axis X-X of the turbomachine so that its inner crenellations 32 come into axial contact with the outer slots 20 of the flange.
  • This type of assembly of the fan disk 10 has certain disadvantages.
  • the rotation of the disc 10 causes low deflections of the retaining ring 30 which cause wear on the top of the outer slots 20 of the flange 18 of the disc.
  • the retaining ring 30 tends to pivot around the flange of the disc with the risk of disengagement of the ring.
  • Such a device consists of a stop element 38 made of elastomeric material intended to be housed, on the one hand axially between two adjacent outer crenellations 20 of the flange 18 of the disk 10 and two adjacent inner crenellations 32 complementary to the ring. 30, and secondly radially between the flange 18 and the retaining ring 30.
  • This abutment element 38 which is shown in FIG. 5, is substantially parallelepipedal and has contact surfaces 40. which are intended to come into contact, on the one hand with the adjacent slots 20 and 32 between which it is mounted, and on the other hand with an inner surface of the retaining ring 30 and with the flange 18 of the rotary disc 10 .
  • the contact surfaces 40 of the abutment element 38 made of elastomeric material deform and come to press against the retaining ring 30 and the flange 18 of the disc. marrying their contours. This deformation of the contact surfaces 40 is shown schematically in FIG. 6 by the arrows F1.
  • contact surfaces between the stop element 38 and the retention ring 30 and the flange 18 of the disc 10 makes it possible to modify the natural modes of vibration of the retention ring.
  • the contact surfaces 40 of the abutment member 38 are deformed and therefore dampen the vibrations experienced by the retention ring. In this way, any risk of wear is avoided.
  • the abutment element 38 By deformation of its contact surfaces 40, the abutment element 38 also makes it possible to ensure tangential locking of the retaining ring 30 around the flange 18 of the disc 10, as shown schematically by the arrows F2 of FIG. 6.
  • Figures 7A and 7B show alternative embodiments of the stop member forming the vibration damping device.
  • the abutment element 38 'of elastomer material is substantially identical to that of FIG. 5 with, in addition, two grooves 42 hollowed longitudinally in the material. These grooves 42 serve to facilitate the extraction of these stop elements.
  • the abutment element 38 "of FIG. 7B further comprises two plates 44 which are intended to come into contact with the inner surface of the retention ring. of this embodiment makes it possible to "foolproof" the stop element when it is mounted on the disk, ie with such a shape, the stop element can not be mounted on the record only in one direction.
  • the elastomeric material of the abutment members 38, 38 'and 38 may be for example a silicone (50D6 / 50D7, 50D8), a fluorosilicone or a fluorocarbon or any other material with equivalent properties.
  • the elastomeric material of the abutment element 38, 38 'and 38 has a hardness of between 50 and 90 shore.
  • the number and angular disposition of the vibration damping devices mounted on the disk may vary.
  • damping devices mount a greater or lesser number of damping devices on the disk; the minimum number being two and the maximum number corresponding to the number of available slots on the disk (that is to say the number of vanes supported by the disk).
  • the number of damping devices is less than that of the blades, these devices may or may not be distributed equidistantly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06117009A 2005-07-21 2006-07-12 Vibrationsdämpfungselemente für einen axialen Haltering von Bläserschaufeln einer Turbomaschine Active EP1746250B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0507753A FR2888897B1 (fr) 2005-07-21 2005-07-21 Dispositif d'amortissement des vibrations d'un anneau de retention axiale des aubes de soufflante d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1746250A1 true EP1746250A1 (de) 2007-01-24
EP1746250B1 EP1746250B1 (de) 2008-09-10

Family

ID=36216780

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06117009A Active EP1746250B1 (de) 2005-07-21 2006-07-12 Vibrationsdämpfungselemente für einen axialen Haltering von Bläserschaufeln einer Turbomaschine

Country Status (8)

Country Link
US (1) US7458769B2 (de)
EP (1) EP1746250B1 (de)
JP (1) JP5005975B2 (de)
CN (1) CN1900533B (de)
CA (1) CA2552287C (de)
DE (1) DE602006002673D1 (de)
FR (1) FR2888897B1 (de)
RU (1) RU2392500C2 (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2948725A1 (fr) * 2009-07-28 2011-02-04 Snecma Dispositif anti-usure d'un rotor de turbomachine
FR2967721A1 (fr) * 2010-11-18 2012-05-25 Snecma Procede de montage d'un module de turbomachine d'aeronef comprenant un tambour portant deux rangees annulaires d'aubes mobiles
FR2971822A1 (fr) * 2011-02-21 2012-08-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
EP2503098A3 (de) * 2011-03-21 2015-02-25 United Technologies Corporation Rotorscheibenanordnung und Sperranordnung dafür
FR3029962A1 (fr) * 2014-12-11 2016-06-17 Snecma Blocage axial des aubes dans une roue de turbomachine
EP3473810A1 (de) * 2017-10-18 2019-04-24 United Technologies Corporation Abgestimmter haltering für eine rotorscheibe

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007247407A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
US20080273982A1 (en) * 2007-03-12 2008-11-06 Honeywell International, Inc. Blade attachment retention device
FR2939832B1 (fr) * 2008-12-11 2011-01-07 Turbomeca Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.
DE102009011964A1 (de) * 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Rotor für eine Strömungsmaschine
FR2945074B1 (fr) 2009-04-29 2011-06-03 Snecma Cale d'aube de soufflante renforcee
DE102010015404B4 (de) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
US9151170B2 (en) * 2011-06-28 2015-10-06 United Technologies Corporation Damper for an integrally bladed rotor
US9261112B2 (en) * 2012-04-24 2016-02-16 General Electric Company Dampers for fan spinners of aircraft engines
EP2706242A1 (de) * 2012-09-11 2014-03-12 Techspace Aero S.A. Befestigung von Laufradschaufeln auf einer Rotortrommel eines Axialkompressors
FR3001402B1 (fr) * 2013-01-31 2015-07-03 Snecma Dispositif auxiliaire de soudage de disques broches, comprenant une ceinture amortissante, et procede de soudage par friction
EP2964522B1 (de) * 2013-03-06 2021-06-16 Raytheon Technologies Corporation Nasenhaubenbefestigung für gasturbinenmotor
US9567857B2 (en) * 2013-03-08 2017-02-14 Rolls-Royce North American Technologies, Inc. Turbine split ring retention and anti-rotation method
FR3003294B1 (fr) * 2013-03-15 2018-03-30 Safran Aircraft Engines Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
JP6229837B2 (ja) * 2013-12-24 2017-11-15 三菱日立パワーシステムズ株式会社 静翼セグメント、及びこれを備えている軸流流体機械
KR102182102B1 (ko) * 2014-11-27 2020-11-23 한화에어로스페이스 주식회사 터빈 장치
US10436032B2 (en) * 2016-05-03 2019-10-08 Pratt & Whitney Canada Corp. Damper ring
US10450865B2 (en) 2016-05-27 2019-10-22 Pratt & Whitney Canada Corp. Friction damper
US10502061B2 (en) 2016-09-28 2019-12-10 Pratt & Whitney Canada Corp. Damper groove with strain derivative amplifying pockets
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
US20180320522A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10865646B2 (en) 2017-05-04 2020-12-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
CN106958537B (zh) * 2017-05-08 2023-06-06 珠海格力电器股份有限公司 蜗壳和空调器
FR3075284B1 (fr) * 2017-12-18 2020-09-04 Safran Aircraft Engines Dispositif amortisseur
US10738630B2 (en) 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
CN108917303B (zh) * 2018-09-26 2023-02-24 珠海格力电器股份有限公司 风机组件、风机及烘干机
FR3106615B1 (fr) * 2020-01-23 2021-12-31 Safran Aircraft Engines Ensemble pour turbomachine
US11525464B2 (en) 2021-03-23 2022-12-13 Pratt & Whitney Canada Corp. Rotor with centrifugally wedged damper
US11391157B1 (en) 2021-03-23 2022-07-19 Pratt & Whitney Canada Corp. Damped rotor assembly
FR3127983A1 (fr) * 2021-10-12 2023-04-14 Safran Aircraft Engines Rotor de turbomachine amélioré
FR3127982A1 (fr) * 2021-10-13 2023-04-14 Safran Aircraft Engines Ensemble d’anneau mobile pour rotor de turbomachine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1096107A2 (de) * 1999-10-27 2001-05-02 Rolls-Royce Plc Verdrehsicherung
FR2803623A1 (fr) * 2000-01-06 2001-07-13 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
US20030194318A1 (en) * 2002-04-16 2003-10-16 Duesler Paul W. Axial retention system and components thereof for a bladed rotor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB928349A (en) * 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
BE792286A (fr) * 1971-12-06 1973-03-30 Gen Electric Dispositif de retenue d'aubes sans boulon pour un rotor de turbomachin
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
FR2663997B1 (fr) * 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
JPH08159281A (ja) * 1994-12-07 1996-06-21 Nissan Diesel Motor Co Ltd 変速機の変速機構
FR2817289B1 (fr) * 2000-11-30 2003-01-31 Snecma Moteurs Dispositif de centrage d'un tube dans un arbre de turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1096107A2 (de) * 1999-10-27 2001-05-02 Rolls-Royce Plc Verdrehsicherung
FR2803623A1 (fr) * 2000-01-06 2001-07-13 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
US20030194318A1 (en) * 2002-04-16 2003-10-16 Duesler Paul W. Axial retention system and components thereof for a bladed rotor

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2948725A1 (fr) * 2009-07-28 2011-02-04 Snecma Dispositif anti-usure d'un rotor de turbomachine
US8573944B2 (en) 2009-07-28 2013-11-05 Snecma Anti-wear device of a turbomachine rotor
FR2967721A1 (fr) * 2010-11-18 2012-05-25 Snecma Procede de montage d'un module de turbomachine d'aeronef comprenant un tambour portant deux rangees annulaires d'aubes mobiles
FR2971822A1 (fr) * 2011-02-21 2012-08-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
WO2012114032A1 (fr) * 2011-02-21 2012-08-30 Snecma Rotor de soufflante et turboréacteur associé
RU2594037C2 (ru) * 2011-02-21 2016-08-10 Снекма Ротор вентилятора и турбореактивный двигатель
US9540935B2 (en) 2011-02-21 2017-01-10 Snecma Fan rotor and associated turbojet engine
EP2503098A3 (de) * 2011-03-21 2015-02-25 United Technologies Corporation Rotorscheibenanordnung und Sperranordnung dafür
FR3029962A1 (fr) * 2014-12-11 2016-06-17 Snecma Blocage axial des aubes dans une roue de turbomachine
EP3473810A1 (de) * 2017-10-18 2019-04-24 United Technologies Corporation Abgestimmter haltering für eine rotorscheibe
US10458244B2 (en) 2017-10-18 2019-10-29 United Technologies Corporation Tuned retention ring for rotor disk

Also Published As

Publication number Publication date
FR2888897A1 (fr) 2007-01-26
RU2006126401A (ru) 2008-01-27
US20070020089A1 (en) 2007-01-25
RU2392500C2 (ru) 2010-06-20
US7458769B2 (en) 2008-12-02
FR2888897B1 (fr) 2007-10-19
CN1900533B (zh) 2011-09-07
CA2552287C (fr) 2013-02-19
CA2552287A1 (fr) 2007-01-21
EP1746250B1 (de) 2008-09-10
JP5005975B2 (ja) 2012-08-22
CN1900533A (zh) 2007-01-24
DE602006002673D1 (de) 2008-10-23
JP2007032564A (ja) 2007-02-08

Similar Documents

Publication Publication Date Title
EP1746250B1 (de) Vibrationsdämpfungselemente für einen axialen Haltering von Bläserschaufeln einer Turbomaschine
EP1584784B1 (de) Einrichtung zur Montage von ringförmigen Flanschen, insbesondere in Turbomaschinen
CA2503011C (fr) Dispositif de retenue axiale d'aubes sur un disque de rotor d'une turbomachine
EP0110744B1 (de) Radial- und Axialbefestigung einer Verdichterschaufel
EP1873401B1 (de) Strömungsmaschinenrotor und Strömungsmaschine
EP0214875B1 (de) Dämpfungselement zur Begrenzung der Auslenkung von Rotorschaufeln einer Turbomaschine
EP0695856B1 (de) Kompressor-Robotscheibe mit asymmetrischer Umfangsnut
FR2973003A1 (fr) Dispositif d'obturation a verrouillage auto-activable
EP2577091B1 (de) Winkeldämpfungsvorrichtung mit je nach drehgeschwindigkeit variabler reibungsvorrichtung
FR2986836A1 (fr) Tole annulaire anti-usure pour une turbomachine
FR2890105A1 (fr) Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et motor d'aeronef les comportant
EP2053199B1 (de) Rad eines Turbotriebwerks
FR2973464A1 (fr) Volant moteur equipe de moyens de retenue des vis de fixation sur le vilebrequin
EP2409044B1 (de) Ausrückbarer axialanschlag
FR3117999A1 (fr) Dispositif de freinage d’une roue d’aéronef ; roue, train d’atterrissage et aéronef équipés d’un tel dispositif.
FR2985294A1 (fr) Dispositif a engagement automatique de freinage d'un arbre rotatif monte rotatif sur un chassis
EP2462361B1 (de) Vorspannungsvorrichtung mit radialer aktivität
FR2556427A1 (fr) Dispositif de liaison a bague de tolerance
WO1986004396A1 (fr) Dispositif d'action centrifuge notamment pour friction d'embrayage
FR2926613A1 (fr) Disque de soufflante de turbomachine
FR3093533A1 (fr) dispositif d’amortissement pour rotor de turbomachine
FR2480378A1 (fr) Mecanisme d'embrayage a diaphragme, notamment pour vehicule automobile, et couvercle propre a la constitution d'un tel mecanisme
FR2544819A1 (fr) Fixation des garnitures de frottement sur un disque de friction, notamment pour embrayage de vehicule automobile
FR2930232A1 (fr) Ensemble pour cycle, fourche et cadre correspondants.
FR3000150A1 (fr) Palier de roulement et systeme de blocage axial dudit palier de roulement

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: 20060712

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB NL

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB NL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602006002673

Country of ref document: DE

Date of ref document: 20081023

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20090611

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006002673

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE GBR, DE

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

Ref country code: GB

Payment date: 20240620

Year of fee payment: 19

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

Ref country code: NL

Payment date: 20240619

Year of fee payment: 19

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

Ref country code: FR

Payment date: 20240619

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20240619

Year of fee payment: 19