EP2464828A1 - Schwingungsdämpfendes abstandsblech für einen ventilatorflügel - Google Patents

Schwingungsdämpfendes abstandsblech für einen ventilatorflügel

Info

Publication number
EP2464828A1
EP2464828A1 EP10739952A EP10739952A EP2464828A1 EP 2464828 A1 EP2464828 A1 EP 2464828A1 EP 10739952 A EP10739952 A EP 10739952A EP 10739952 A EP10739952 A EP 10739952A EP 2464828 A1 EP2464828 A1 EP 2464828A1
Authority
EP
European Patent Office
Prior art keywords
upstream
downstream
platform
disk
fan
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
EP10739952A
Other languages
English (en)
French (fr)
Other versions
EP2464828B1 (de
Inventor
Laurent Bilz
Fabrice Marois
Patrick Jean-Louis Reghezza
Julien Tran
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 EP2464828A1 publication Critical patent/EP2464828A1/de
Application granted granted Critical
Publication of EP2464828B1 publication Critical patent/EP2464828B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • 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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping 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
    • 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
    • F01D5/3053—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
    • 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
    • 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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates generally to a fan for an aircraft turbomachine, preferably for a turbojet engine. More specifically, the invention relates vibration damping wedges interposed between the blade platform and the fan disk.
  • FIG. 1 A blower 1 for a turbojet engine known from the prior art is shown in FIG. 1. It has a disk 2 centered on a longitudinal axis 4, corresponding to the axis of rotation of the fan. Blower vanes 6 are mounted at the periphery of the disc in a conventional manner and regularly distributed around the axis 4.
  • vibration damping wedge 10 interposed radially between the platform 12 of the blade and the periphery of the disk 2.
  • this wedge takes the form of an elastomer block 14 equipped contact pads 16a, 16b provided to reduce the vibration levels of the fan blades.
  • the shim 10 is provided with a radially outer surface 18 equipped with two plates 16a, 16b of contact with the platform 12, as well as with a radially inner surface 20 formed by an upstream surface 22 facing the disc 2 and a downstream surface 24 separated from the upstream surface by a recess or level 26.
  • upstream and downstream are to consider with respect to a direction of thrust generated by the fan, shown schematically by the arrow 5.
  • the upstream surface 22 is located radially inward with respect to the downstream surface 24.
  • the upstream surface 22 is centered on a transverse median plane of the disc 2 opposite which it is located.
  • the downstream surface 24 is located radially right and facing a fastening flange 28 provided in one piece with the disk, and protruding radially outwards. This flange 28 permits the bolt mounting of an axial abutment shim 30 preventing the vibration damping wedge 10 from escaping backward.
  • the shim 30 has a radially outer flange 32 against which is abutted an axial abutment plate 34 provided on the shim 10, at the radially upper portion of its downstream end surface 36.
  • the stop plate 34 also extends to the downstream surface 24, thereby adopting an inverted L-shaped section.
  • the stop plate is preferably metallic.
  • each flange 28 is provided in one piece with a radial tooth 23 of the disc 2, these teeth 23 being spaced circumferentially from each other and defining between them notches intended to accommodate the blade root 6.
  • one or more material recesses 40 open axially and each housing a portion of a bolt 42 for mounting of the stop block 30 on the flange 28.
  • the recess 26 comparable to a radially facing surface facing downstream, constitutes a demarcation on either side of which are respectively the upstream plate 16a contact with the platform and the downstream contact plate 16b with the same platform.
  • each wedge 10 can extend over an angular sector of only a few degrees.
  • the wrong positioning occupied by the wedge 10 can cause its premature wear as well as that of the parts in contact.
  • the forward tilting of the shim 10 has the usual consequence of the loss of contact between the axial abutment plate 34 and its associated abutment shim 30, and the loss of contact between the upstream contact plate 16a and its associated portion of the platform.
  • a very high intensity contact then remains between the downstream contact pad 16b and its associated portion of the platform, as well as between the upstream end or edge 22a of the upstream surface 22 and the disk 2, with consequent risks. premature wear mentioned above.
  • the subject of the invention is a vibration damping wedge intended to be interposed between a fan blade platform and a fan disk, said wedge being provided with a radially outer surface equipped with at least one plate contact with the fan blade platform, and a radially inner surface formed by an upstream surface intended to be opposite said disk and a downstream surface separated from the upstream surface by a recess, said upstream surface being located radially towards the interior with respect to said downstream surface.
  • said upstream surface has a radially inwardly projecting zone, initiated at a distance from its upstream end.
  • this protruding zone makes it possible to limit the amplitude of the tilting of the wedge described above, because this zone is located closest to the periphery of the disk with which it is capable of rapidly coming to a stop, when Insufficient centrifugal force does not make it possible to obtain the plating of the radially outer surface of the damping wedge against the platform.
  • this limitation of the tilting amplitude of the shim results from the position downstream of the projecting zone.
  • this edge when contact occurs between the upstream edge of the projecting zone and the disc, following a limited tilting of the wedge towards the front, this edge is at a low angle limiting its wear. Indeed, this low angle is synonymous with significant contact surface between the edge and the disc, limiting the risk of premature wear of the hold.
  • the position of the projecting zone, at a distance from the upstream end of the upstream surface and upstream of the recess makes it possible not to unbalance the shim in its entirety, which makes it possible to find its center of gravity in the same area in which it was on the damping wedges of the prior art with substantially flat upstream surface.
  • the damping wedge comprises an upstream plate of contact with the fan blade platform and a downstream contact plate with the fan blade platform, respectively arranged upstream and downstream relative to said recess.
  • said protruding zone is located radially in line with said upstream contact plate.
  • the damping wedge comprises a downstream end surface, a radially upper portion of which is equipped with an axial abutment plate.
  • said projecting zone extends axially over approximately 40 to 70% of said upstream surface of the radially inner surface.
  • said recess has one or more material recesses open axially downstream.
  • the invention also relates to an aircraft turbomachine fan comprising a fan disk and a plurality of fan blades mounted on the disk, each blade having a platform and at least one vibration damping shim such as as described above, interposed between said platform and the disk.
  • a single vibration damping wedge is placed under a same fan blade.
  • FIGS. 1 and 2 already described, represent an aircraft jet engine blower known from the prior art
  • FIG. 3 represents an aircraft turbojet fan according to a preferred embodiment of the present invention.
  • FIG. 4 and 5 show two perspective views of the vibration damping wedge equipping the fan of Figure 3, according to two different angles of view.
  • FIGS. 3 and 4 it is possible to see a fan 1 of an aircraft turbojet according to a preferred embodiment of the present invention.
  • This blower differs from that described in Referring to Figures 1 and 2 only by the shape of the upstream surface 22 of the vibration damping shim 10.
  • the elements bearing the same reference numerals correspond to identical or similar elements.
  • the upstream surface 22 located upstream of the recess 26 is no longer flat or slightly curved as in the prior art, but has a region 101 projecting radially inward, initiated at a distance from its upstream end 22a.
  • the upstream surface 22 of the radially inner surface 20 begins with a recess 103 initiated from the upstream end or edge 22a, then encounters a radially inwardly directed recess 105 which initiates the projecting zone 101. This extends downstream to the detachment 26.
  • the recess 103 and the projecting zone 101 each have a substantially flat surface facing the disc 2, or slightly curved inwards to follow the profile of this disc. They therefore each extend homogeneously along the circumferential direction of the shim, at different distances from the disk 2, the zone 101 being closer.
  • the projecting zone 101 extends axially over approximately 40 to 70% of the upstream surface 22, and lies at the right, in the radial direction, of the upstream contact plate 16a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10739952.9A 2009-08-11 2010-08-09 Schwingungsdämpfendes abstandsblech für einen ventilatorflügel Active EP2464828B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0955625A FR2949142B1 (fr) 2009-08-11 2009-08-11 Cale amortisseuse de vibrations pour aube de soufflante
PCT/EP2010/061534 WO2011018425A1 (fr) 2009-08-11 2010-08-09 Cale amortisseuse de vibrations pour aube de soufflante

Publications (2)

Publication Number Publication Date
EP2464828A1 true EP2464828A1 (de) 2012-06-20
EP2464828B1 EP2464828B1 (de) 2016-10-05

Family

ID=42040528

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10739952.9A Active EP2464828B1 (de) 2009-08-11 2010-08-09 Schwingungsdämpfendes abstandsblech für einen ventilatorflügel

Country Status (9)

Country Link
US (1) US8911210B2 (de)
EP (1) EP2464828B1 (de)
JP (1) JP5702783B2 (de)
CN (1) CN102472108B (de)
BR (1) BR112012002909B1 (de)
CA (1) CA2769781C (de)
FR (1) FR2949142B1 (de)
RU (1) RU2539924C2 (de)
WO (1) WO2011018425A1 (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
FR3003294B1 (fr) * 2013-03-15 2018-03-30 Safran Aircraft Engines Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
US20150117804A1 (en) * 2013-10-30 2015-04-30 United Technologies Corporation Gas turbine engine bushing
EP3073052B1 (de) * 2015-02-17 2018-01-24 Rolls-Royce Corporation Bläserbaugruppe
US10385701B2 (en) * 2015-09-03 2019-08-20 General Electric Company Damper pin for a turbine blade
FR3047512B1 (fr) * 2016-02-05 2019-11-15 Safran Aircraft Engines Dispositif d'amortissement de vibrations pour aubes de turbomachine
FR3048997B1 (fr) * 2016-03-21 2020-03-27 Safran Aircraft Engines Plateforme d'aube et disque de soufflante de turbomachine aeronautique
RU175943U1 (ru) * 2016-09-19 2017-12-25 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Ротор турбины
EP3724453A1 (de) * 2017-12-12 2020-10-21 Safran Helicopter Engines Schwingungsdämpfer für eine turbomaschinenrotorschaufel
FR3075282B1 (fr) * 2017-12-14 2021-01-08 Safran Aircraft Engines Dispositif amortisseur
US10927683B2 (en) 2017-12-14 2021-02-23 Safran Aircraft Engines Damping device
WO2019122691A1 (fr) 2017-12-18 2019-06-27 Safran Aircraft Engines Dispositif amortisseur
FR3075284B1 (fr) 2017-12-18 2020-09-04 Safran Aircraft Engines Dispositif amortisseur
FR3075253B1 (fr) * 2017-12-20 2019-11-22 Safran Aircraft Engines Dispositif amortisseur
DE102018221533A1 (de) * 2018-12-12 2020-06-18 MTU Aero Engines AG Turbomaschinen Schaufelanordnung
FR3096731B1 (fr) 2019-05-29 2021-05-07 Safran Aircraft Engines Ensemble pour turbomachine
FR3096734B1 (fr) 2019-05-29 2021-12-31 Safran Aircraft Engines Ensemble pour turbomachine
EP3976929A1 (de) 2019-05-29 2022-04-06 Safran Aircraft Engines Anordnung für eine turbomaschine
FR3096732A1 (fr) 2019-05-29 2020-12-04 Safran Aircraft Engines Ensemble pour turbomachine
FR3096729B1 (fr) 2019-05-29 2021-04-30 Safran Aircraft Engines Ensemble pour turbomachine
FR3096733B1 (fr) 2019-05-29 2022-11-18 Safran Aircraft Engines Ensemble pour turbomachine
FR3096730B1 (fr) 2019-05-29 2021-04-30 Safran Aircraft Engines Ensemble pour turbomachine
FR3099213B1 (fr) 2019-07-23 2021-07-16 Safran Aircraft Engines Rotor de soufflante pour une turbomachine d’aeronef
FR3126447A1 (fr) * 2021-08-30 2023-03-03 Safran Aircraft Engines Roue mobile de turbomachine comprenant une pièce de butée axiale pour amortisseur
FR3126446A1 (fr) * 2021-09-01 2023-03-03 Safran Aircraft Engines Amortisseur déformable pour roue mobile de turbomachine

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Also Published As

Publication number Publication date
BR112012002909A2 (pt) 2016-04-05
RU2012108735A (ru) 2013-09-20
JP2013501883A (ja) 2013-01-17
EP2464828B1 (de) 2016-10-05
CA2769781A1 (fr) 2011-02-17
US20120141296A1 (en) 2012-06-07
CA2769781C (fr) 2017-07-25
WO2011018425A1 (fr) 2011-02-17
RU2539924C2 (ru) 2015-01-27
JP5702783B2 (ja) 2015-04-15
BR112012002909B1 (pt) 2020-06-16
FR2949142B1 (fr) 2011-10-14
CN102472108A (zh) 2012-05-23
FR2949142A1 (fr) 2011-02-18
CN102472108B (zh) 2014-12-31
US8911210B2 (en) 2014-12-16

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