EP1746250B1 - Dispositif d'amortissement des vibrations d'un anneau de rétention axiale des aubes de soufflante d'une turbomachine - Google Patents

Dispositif d'amortissement des vibrations d'un anneau de rétention axiale des aubes de soufflante d'une turbomachine Download PDF

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Publication number
EP1746250B1
EP1746250B1 EP06117009A EP06117009A EP1746250B1 EP 1746250 B1 EP1746250 B1 EP 1746250B1 EP 06117009 A EP06117009 A EP 06117009A EP 06117009 A EP06117009 A EP 06117009A EP 1746250 B1 EP1746250 B1 EP 1746250B1
Authority
EP
European Patent Office
Prior art keywords
flange
disk
retention ring
crenellations
ring
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
EP06117009A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1746250A1 (fr
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/fr
Application granted granted Critical
Publication of EP1746250B1 publication Critical patent/EP1746250B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 mounting the fan blades on a rotating disk of a turbomachine as described in document US 2003/194 318 A . 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 disadvantages 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 against the retention ring by centrifugal effect. 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.
  • the figures 1 and 2 partially represent a disk 10 of turbomachine blower. This disc 10 is able to rotate about the longitudinal axis XX of the turbomachine.
  • the rotary 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 represented on the outer circumference). figure 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 stop element 38 which is represented on the figure 5 , is substantially parallelepipedic 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 schematized on the figure 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 provide a tangential blocking of the retaining ring 30 around the flange 18 of the disc 10, as shown schematically by the arrows F 2 of the figure 6 .
  • FIGS. 7A and 7B represent alternative embodiments of the stop element forming the vibration damping device.
  • the abutment element 38 'of elastomer material is substantially identical to that of the figure 5 with further two grooves 42 hollowed longitudinally in the material. These grooves 42 serve to facilitate the extraction of these stop elements.
  • the stop element 38 "of the Figure 7B further comprises two plates 44 which are intended to come into contact with the inner surface of the retention ring.
  • the particular geometrical shape of this embodiment makes it possible to "fool out” the stop element when it is mounted on the disk; that is, with such a shape, the stop member can be mounted on the disc 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. On the example of figures 1 and 2 representing an angular sector of the disk of 90 °, it is thus provided 3 damping devices for 7 blades, or 12 devices on the entire disk supporting a total of 28 blades.
  • 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.

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  • 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 Dispositif d'amortissement des vibrations d'un anneau de rétention axiale des aubes de soufflante d'une turbomachine Active EP1746250B1 (fr)

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 EP1746250A1 (fr) 2007-01-24
EP1746250B1 true EP1746250B1 (fr) 2008-09-10

Family

ID=36216780

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06117009A Active EP1746250B1 (fr) 2005-07-21 2006-07-12 Dispositif d'amortissement des vibrations d'un anneau de rétention axiale des aubes de soufflante d'une turbomachine

Country Status (8)

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

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US20080273982A1 (en) * 2007-03-12 2008-11-06 Honeywell International, Inc. Blade attachment retention device
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FR2945074B1 (fr) 2009-04-29 2011-06-03 Snecma Cale d'aube de soufflante renforcee
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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
FR2967721B1 (fr) * 2010-11-18 2012-12-21 Snecma Procede de montage d'un module de turbomachine d'aeronef comprenant un tambour portant deux rangees annulaires d'aubes mobiles
FR2971822B1 (fr) 2011-02-21 2015-04-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
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Also Published As

Publication number Publication date
DE602006002673D1 (de) 2008-10-23
EP1746250A1 (fr) 2007-01-24
CA2552287A1 (fr) 2007-01-21
FR2888897B1 (fr) 2007-10-19
US20070020089A1 (en) 2007-01-25
RU2006126401A (ru) 2008-01-27
FR2888897A1 (fr) 2007-01-26
CN1900533B (zh) 2011-09-07
JP2007032564A (ja) 2007-02-08
RU2392500C2 (ru) 2010-06-20
CN1900533A (zh) 2007-01-24
CA2552287C (fr) 2013-02-19
US7458769B2 (en) 2008-12-02
JP5005975B2 (ja) 2012-08-22

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