EP1746250B1 - Vibration damping elements for an axial holding ring of turbomachine fan blades - Google Patents

Vibration damping elements for an axial holding ring of turbomachine fan blades Download PDF

Info

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)
French (fr)
Other versions
EP1746250A1 (en
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/en
Application granted granted Critical
Publication of EP1746250B1 publication Critical patent/EP1746250B1/en
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 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.

Landscapes

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

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général du montage des aubes de soufflante sur un disque rotatif d'une turbomachine comme décrit dans le document US 2003/194 318 A . Elle vise plus particulièrement un dispositif permettant d'amortir les vibrations subies par l'anneau de rétention axiale des aubes de soufflante.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.

La soufflante d'une turbomachine se compose typiquement d'une pluralité d'aubes montées sur un disque rotatif par l'intermédiaire de leur pied qui est emmanché dans des évidements du disque. Dans certaines technologies de montage d'aubes de soufflante, un anneau est également disposé autour d'une bride annulaire qui s'étend axialement du côté amont du disque rotatif. Un tel anneau est maintenu axialement contre la bride par l'intermédiaire de créneaux formés sur toute la circonférence de cette dernière. L'anneau est par ailleurs monté en butée axiale contre le pied des aubes afin d'assurer une rétention axiale de ces dernières.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. In certain fan blade mounting technologies, 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.

En pratique, ce type de montage d'aubes de soufflante pose de nombreux problèmes. Notamment, des usures ont été constatées sur l'anneau de rétention axiale et le disque rotatif. Ces usures sont principalement provoquées par les vibrations subies par l'anneau de rétention axiale lors de la rotation du disque. En particulier, la rotation du disque entraîne des faibles débattements de l'anneau de rétention axiale qui provoquent des usures sur le sommet des créneaux de la bride annulaire de maintien de l'anneau sur le disque. En outre, lors de la rotation du disque, l'anneau de rétention axiale a tendance à se déplacer tangentiellement autour de la bride du disque.In practice, this type of fan blade assembly poses many problems. In particular, 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. In particular, 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. In addition, during the rotation of the disc, the axial retention ring tends to move tangentially around the flange of the disc.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant un dispositif d'amortissement des vibrations subies par l'anneau de rétention axiale des aubes de soufflante.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 cet effet, il est prévu un dispositif d'amortissement des vibrations d'un anneau de rétention axiale des aubes de soufflante d'une turbomachine, lesdites aubes de soufflante étant destinées à être montées par leur pied sur un disque rotatif comportant une bride annulaire s'étendant axialement et munie d'une pluralité de créneaux radiaux destinés à venir en contact avec une pluralité de créneaux radiaux complémentaires d'un anneau de rétention destiné à être monté autour de la bride du disque, ledit dispositif étant caractérisé en ce qu'il se compose d'un élément de butée en matériau élastomère destiné à venir se loger axialement entre deux créneaux adjacents de la bride et deux créneaux adjacents complémentaires de l'anneau de rétention et radialement entre la bride du disque rotatif et l'anneau de rétention, ledit élément de butée présentant des surfaces de contact destinées à venir en contact avec lesdits créneaux adjacents, l'anneau de rétention et la bride du disque rotatif.For this purpose, there is provided 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.

Par l'ajout de surfaces de contact avec l'anneau de rétention axiale et la bride du disque, le dispositif selon l'invention permet de modifier les modes propres de vibration de l'anneau de rétention. En outre, ce dispositif étant constitué d'un élément en matériau élastomère, les surfaces de ce dernier qui sont en contact avec l'anneau de rétention et la bride du disque ont tendance à venir se plaquer par effet centrifuge contre l'anneau de rétention et la bride. Ainsi, les vibrations subies par l'anneau de rétention sont amorties et tout risque d'usure est écarté. L'utilisation d'un tel dispositif d'amortissement permet également d'assurer un blocage tangentiel de l'anneau de rétention autour de la bride du disque.By adding contact surfaces with the axial retention ring and the disc flange, the device according to the invention makes it possible to modify the natural modes of vibration of the retention ring. In addition, 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. Thus, 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.

L'élément de butée du dispositif d'amortissement peut être sensiblement parallélépipédique. Il peut également présenter une forme géométrique destinée à assurer son détrompage lors de son montage sur le disque.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.

De préférence, le matériau élastomère de l'élément de butée présente une dureté comprise entre 50 et 90 shore. Ce matériau élastomère est de préférence un silicone, un fluorosilicone ou un fluorocarbone.Preferably, 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.

L'invention a aussi pour objet un anneau de rétention axiale des aubes de soufflante d'une turbomachine comportant au moins un dispositif d'amortissement des vibrations précités.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.

L'invention a également pour objet un disque rotatif de turbomachine pour le montage d'aubes de soufflante, comportant une bride annulaire s'étendant axialement et munie d'une pluralité de créneaux radiaux destinés à venir en contact avec une pluralité de créneaux radiaux complémentaires d'un anneau de rétention axiale des aubes de soufflante destiné à être monté autour de la bride du disque, le disque comporte en outre au moins deux dispositifs d'amortissement tels que définis précédemment. Enfin, l'invention a pour objet une turbomachine comportant au moins un disque rotatif tel que défini précédemment.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. Finally, the subject of the invention is a turbomachine comprising at least one rotating disk as defined above.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue partielle, en perspective et en éclaté d'un disque de soufflante équipé d'un dispositif d'amortissement des vibrations selon l'invention ;
  • la figure 2 est une vue du disque de la figure 1 monté ;
  • les figures 3 et 4 sont des vues en coupe de la figure 2, respectivement selon III-III et IV-IV ;
  • la figure 5 est une vue en perspective du dispositif d'amortissement des vibrations de la figure 1 ;
  • la figure 6 est une loupe d'un détail de la figure 2 ; et
  • les figures 7A et 7B sont des vues en perspective de dispositifs d'amortissement des vibrations selon d'autres modes de réalisation de l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a partial view, in perspective and exploded of a fan disk equipped with a vibration damping device according to the invention;
  • the figure 2 is a view of the disc of the figure 1 mounted;
  • the Figures 3 and 4 are sectional views of the figure 2 respectively according to III-III and IV-IV;
  • the figure 5 is a perspective view of the vibration damping device of the figure 1 ;
  • the figure 6 is a magnifying glass of a detail of the figure 2 ; and
  • the Figures 7A and 7B are perspective views of vibration damping devices according to other embodiments of the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

Les figures 1 et 2 représentent partiellement un disque 10 de soufflante de turbomachine. Ce disque 10 est apte à tourner autour de l'axe longitudinal X-X de la turbomachine.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.

Le disque rotatif 10 comporte une pluralité d'évidements 12 régulièrement répartis sur toute sa circonférence extérieure, chaque évidement étant destiné à recevoir le pied 14 d'une aube 16 de soufflante (une seule aube est partiellement représentée sur la figure 1). Plus précisément, le pied 14 de chaque aube 16 présente une forme de queue d'aronde qui vient s'emmancher axialement dans les évidements 12 prévus à cet effet.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 ). Specifically, the foot 14 of each blade 16 has a shape of dovetail which is axially slip into the recesses 12 provided for this purpose.

Le disque rotatif 10 comporte également une bride annulaire 18 qui s'étend axialement vers l'amont. A son extrémité opposée au disque, cette bride 18 est munie d'une pluralité de créneaux (ou dents) extérieurs 20 qui s'étendent radialement vers l'extérieur du disque et qui sont régulièrement répartis sur toute la circonférence du disque.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.

On notera que le nombre de créneaux extérieurs 20 de la bride 18 est identique au nombre d'évidements 12 du disque destinés à recevoir les aubes de soufflante 16. Par ailleurs, les créneaux extérieurs 20 sont sensiblement alignés (dans le sens axial) avec ces évidements 12.Note that 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.

A son extrémité opposée au disque 10, la bride 18 est également pourvue d'une collerette annulaire 22 qui s'étend radialement vers l'intérieur du disque (c'est-à-dire vers l'axe X-X de rotation de ce dernier). Cette collerette 22 comporte des orifices 24 répartis sur toute sa circonférence. Elle est destinée à recevoir un flasque annulaire 26 maintenu contre celle-ci à l'aide de vis 28 venant se loger dans les orifices 24. Le rôle d'un tel flasque est de bloquer le déplacement tangentiel de l'anneau et de remplir d'autres fonctions au sein de la soufflante de turbomachine (notamment tenir les plateformes inter-aubes).At its end opposite the disk 10, 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).

Un anneau 30 de rétention axiale des aubes 16 est destiné à être monté autour de la bride 18 du disque 10. Cet anneau de rétention 30 comporte une pluralité de créneaux (ou dents) intérieurs 32 s'étendant radialement vers l'intérieur du disque qui sont destinés à venir en contact axial avec les créneaux extérieurs 20 de la bride 18 lorsque l'anneau est monté autour de cette dernière. Le nombre de créneaux de la bride et de l'anneau de rétention est donc identique.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.

Par ailleurs, l'anneau de rétention 30 est muni de créneaux (ou dents) extérieurs 34 qui s'étendent radialement vers l'extérieur du disque et qui sont alignés radialement avec ses créneaux intérieurs 32. Lorsque l'anneau de rétention 30 est monté sur la bride, ces créneaux extérieurs 34 sont destinés à venir en butée axiale avec des éléments de butée 36 montés contre chaque pied 14 d'aube.Furthermore, 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. When the retaining ring 30 is mounted on the flange, these outer slots 34 are intended to come into axial abutment with abutment members 36 mounted against each blade root 14.

Comme illustré par les figures 3 et 4, l'anneau de rétention 30 est maintenu axialement sur la bride 18 du disque par le contact entre ses créneaux intérieurs 32 et les créneaux extérieurs 20 de la bride. Par l'intermédiaire de ses créneaux extérieurs 34 qui sont en butée axiale contre les éléments de butée 36, l'anneau de rétention peut ainsi assurer un maintien axial des pieds 14 d'aube dans leurs évidements 12 respectifs.As illustrated by Figures 3 and 4 , 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. By means of its outer slots 34 which are in axial abutment against the abutment members 36, the retention ring can thus ensure an axial retention of the blade roots 14 in their respective recesses 12.

Le montage de l'anneau de rétention 30 sur la bride 18 du disque s'effectue de la manière suivante : l'anneau est centré sur l'axe longitudinal X-X de la turbomachine avec ses créneaux intérieurs 32 décalés axialement par rapport aux créneaux extérieurs 20 de la bride 18 du disque. Par translation axiale, l'anneau est amené autour de la bride, chacun de ses créneaux intérieurs 32 s'insérant entre deux créneaux extérieurs 20 adjacents de la bride. Une fois monté, l'anneau est alors pivoté autour de l'axe longitudinal X-X de la turbomachine afin que ses créneaux intérieurs 32 viennent en contact axial avec les créneaux extérieurs 20 de la bride.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. By axial translation, the ring is brought around the flange, each of its inner crenellations 32 inserted between two adjacent outer crenellations 20 of the flange. Once mounted, 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.

Ce type d'assemblage du disque de soufflante 10 présente certains inconvénients. D'une part, la rotation du disque 10 entraîne des faibles débattements de l'anneau de rétention 30 qui provoquent des usures sur le sommet des créneaux extérieurs 20 de la bride 18 du disque. En outre, lors de la rotation du disque, l'anneau de rétention 30 a tendance à pivoter autour de la bride du disque avec le risque d'un désengagement de l'anneau.This type of assembly of the fan disk 10 has certain disadvantages. On the one hand, 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. In addition, during the rotation of the disc, the retaining ring 30 tends to pivot around the flange of the disc with the risk of disengagement of the ring.

Selon l'invention, il est prévu un dispositif d'amortissement des vibrations subies par l'anneau de rétention 30 permettant d'éliminer ces inconvénients.According to the invention, there is provided a vibration damping device undergone by the retention ring 30 to eliminate these disadvantages.

Un tel dispositif se compose d'un élément de butée 38 en matériau élastomère destiné à venir se loger, d'une part axialement entre deux créneaux extérieurs 20 adjacents de la bride 18 du disque 10 et deux créneaux intérieurs 32 adjacents complémentaires de l'anneau de rétention 30, et d'autre part radialement entre la bride 18 et l'anneau de rétention 30.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.

Cet élément de butée 38, qui est représenté sur la figure 5, est sensiblement parallélépipédique et présente des surfaces de contact 40 qui sont destinées à venir en contact, d'une part avec les créneaux adjacents 20 et 32 entre lesquels il est monté, et d'autre part avec une surface interne de l'anneau de rétention 30 et avec la bride 18 du disque rotatif 10.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 .

Par effet de la force centrifuge due à la rotation du disque 10, les surfaces de contact 40 de l'élément de butée 38 réalisé en matériau élastomère se déforment et viennent se plaquer contre l'anneau de rétention 30 et la bride 18 du disque en épousant leurs contours. Cette déformation des surfaces de contact 40 est schématisée sur la figure 6 par les flèches F1.By the effect of the centrifugal force due to the rotation of the 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.

L'ajout de surfaces de contact entre l'élément de butée 38 et l'anneau de rétention 30 et la bride 18 du disque 10 permet de modifier les modes propres de vibration de l'anneau de rétention. En outre, les surfaces de contact 40 de l'élément de butée 38 se déforment et viennent donc amortir les vibrations subies par l'anneau de rétention. De la sorte, tout risque d'usure est écarté.The addition of 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. In addition, 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.

Par déformation de ses surfaces de contact 40, l'élément de butée 38 permet également d'assurer un blocage tangentiel de l'anneau de rétention 30 autour de la bride 18 du disque 10 comme schématisé par les flèches F2 de la figure 6.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 .

Les figures 7A et 7B représentent des variantes de réalisation de l'élément de butée formant le dispositif d'amortissement des vibrations.The Figures 7A and 7B represent alternative embodiments of the stop element forming the vibration damping device.

Sur l'exemple de la figure 7A, l'élément de butée 38' en matériau élastomère est sensiblement identique à celui de la figure 5 avec en outre deux rainures 42 creusées longitudinalement dans la matière. Ces rainures 42 ont pour rôle de faciliter l'extraction de ces éléments de butée.On the example of the Figure 7A , 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.

Par rapport au mode de réalisation de la figure 7A, l'élément de butée 38" de la figure 7B comporte en outre deux plats 44 qui sont destinés à venir en contact avec la surface interne de l'anneau de rétention. La forme géométrique particulière de ce mode de réalisation permet d'assurer un « détrompage » de l'élément de butée lors de son montage sur le disque ; c'est-à-dire qu'avec une telle forme, l'élément de butée ne peut être monté sur le disque que dans un seul sens.Compared to the embodiment of the Figure 7A , 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.

Le matériau élastomère des éléments de butée 38, 38' et 38" peut être par exemple un silicone (50D6/50D7, 50D8), un fluorosilicone ou un fluorocarbone ou tout autre matériau aux propriétés équivalentes.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.

De préférence, le matériau élastomère de l'élément de butée 38, 38' et 38" présente une dureté comprise entre 50 et 90 shore.Preferably, the elastomeric material of the abutment element 38, 38 'and 38 "has a hardness of between 50 and 90 shore.

Le nombre et la disposition angulaire des dispositifs d'amortissement des vibrations montés sur le disque peuvent varier. Sur l'exemple des figures 1 et 2 représentant un secteur angulaire du disque de 90°, il ainsi est prévu 3 dispositifs d'amortissement pour 7 aubes, soit 12 dispositifs sur l'ensemble du disque supportant au total 28 aubes.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.

Il est cependant possible de monter un nombre plus ou moins élevé de dispositifs d'amortissement sur le disque ; le nombre minimum étant de deux et le nombre maximum correspondant au nombre d'emplacements disponibles sur le disque (c'est-à-dire au nombre d'aubes supportées par le disque). Lorsque le nombre de dispositifs d'amortissement est inférieur à celui des aubes, ces dispositifs peuvent ou non être répartis de façon équidistante.It is possible, however, to 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). When the number of damping devices is less than that of the blades, these devices may or may not be distributed equidistantly.

Claims (9)

  1. A device for damping vibration of an axial retention ring for retaining fan blades of a turbomachine, said fan blades (16) being designed to be mounted via their roots (14) on a rotary disk (10) including an annular flange (18) extending axially and provided with a plurality of radial crenellations (20) for coming into contact with a plurality of complementary radial crenellations (32) of a retention ring (30) that is to be mounted around said flange (18) of the disk (10), said device being characterized in that it is made up of an abutment element (38, 38', 38") of elastomer material that is to be received axially between two adjacent crenellations (20) of the flange (18) and two adjacent complementary crenellations (32) of the retention ring (30), and radially between the flange (18) of the rotary disk and the retention ring (30), said abutment element (38, 38', 38") presenting contact surfaces (40, 44) for coming into contact with said adjacent crenellations (20, 32), with the retention ring (30), and with the flange (18) of the rotary disk (10).
  2. A device according to claim 1, in which the abutment element (38, 38', 38") is substantially in the form of a flat rectangular block.
  3. A device according to claim 1 or claim 2, in which the abutment element (38, 38', 38") presents a geometrical shape that is designed to prevent error while it is being mounted on the disk (10).
  4. A device according to any one of claims 1 to 3, in which the elastomer material of the abutment element (38, 38', 38") presents hardness lying in the range 50 to 90 on the Shore scale.
  5. A device according to any one of claims 1 to 4, in which the elastomer material of the abutment element (38, 38', 38") is a silicone, a fluorosilicone, or a fluorocarbon.
  6. A rotary disk (10) for a turbomachine for mounting blades of a fan (16), the disk including an annular flange (18) extending axially and provided with a plurality of radial crenellations (20) for coming into contact with a plurality of complementary radial crenellations (32) of a retention ring (30) for axially retaining fan blades and designed to be mounted around the flange (18) of the disk, the disk being characterized in that it includes at least two damper devices according to any one of claims 1 to 5.
  7. A disk according to claim 6, in which the damper devices are equidistant from one another.
  8. A retention ring for axially retaining fan blades of a turbomachine, the ring including at least one vibration damper device according to any one of claims 1 to 5.
  9. A turbomachine including at least one rotary disk according to claim 6 or claim 7.
EP06117009A 2005-07-21 2006-07-12 Vibration damping elements for an axial holding ring of turbomachine fan blades Active EP1746250B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0507753A FR2888897B1 (en) 2005-07-21 2005-07-21 DEVICE FOR DAMPING THE VIBRATION OF AN AXIAL RETAINING RING OF BLOWER BLADES OF A TURBOMACHINE

Publications (2)

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

Family

ID=36216780

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06117009A Active EP1746250B1 (en) 2005-07-21 2006-07-12 Vibration damping elements for an axial holding ring of turbomachine fan blades

Country Status (8)

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

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007247406A (en) * 2006-03-13 2007-09-27 Ihi Corp Holding structure of fan blade
JP2007247407A (en) * 2006-03-13 2007-09-27 Ihi Corp Holding structure of fan blade
US20080273982A1 (en) * 2007-03-12 2008-11-06 Honeywell International, Inc. Blade attachment retention device
FR2939832B1 (en) * 2008-12-11 2011-01-07 Turbomeca TURBINE WHEEL EQUIPPED WITH AXIAL HOLDING DEVICE LOCKING BLADES WITH RESPECT TO A DISK.
DE102009011964A1 (en) * 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Rotor for a turbomachine
FR2945074B1 (en) 2009-04-29 2011-06-03 Snecma REINFORCED BLOW OF BREATHING BLADE
FR2948725B1 (en) 2009-07-28 2012-10-05 Snecma ANTI-WEAR DEVICE FOR A TURBOMACHINE ROTOR
DE102010015404B4 (en) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Method for repairing a rotor assembly of a turbomachine, ring element for a rotor assembly of a turbomachine and rotor assembly for a turbomachine
FR2963806B1 (en) * 2010-08-10 2013-05-03 Snecma DEVICE FOR LOCKING A FOOT OF A ROTOR BLADE
FR2967721B1 (en) * 2010-11-18 2012-12-21 Snecma METHOD FOR MOUNTING AN AIRCRAFT TURBOMACHINE MODULE COMPRISING A DRUM CARRYING TWO ANNUAL ROWS OF MOBILE AUBES
FR2971822B1 (en) * 2011-02-21 2015-04-24 Snecma BLOWER ROTOR, ESPECIALLY FOR A TURBOMACHINE
US8840375B2 (en) * 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
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 (en) * 2012-09-11 2014-03-12 Techspace Aero S.A. Fixing of blades on an axial compressor drum
FR3001402B1 (en) * 2013-01-31 2015-07-03 Snecma AUXILIARY DEVICE FOR WELDING PULP DISCS, COMPRISING A DAMAGING BELT, AND FRICTION WELDING METHOD
US10072509B2 (en) 2013-03-06 2018-09-11 United Technologies Corporation Gas turbine engine nose cone attachment
US9567857B2 (en) * 2013-03-08 2017-02-14 Rolls-Royce North American Technologies, Inc. Turbine split ring retention and anti-rotation method
FR3003294B1 (en) * 2013-03-15 2018-03-30 Safran Aircraft Engines MULTI-FLOW TURBOMOTEUR BLOWER, AND TURBOMOTEUR EQUIPPED WITH SUCH BLOWER
JP6229837B2 (en) * 2013-12-24 2017-11-15 三菱日立パワーシステムズ株式会社 Stator blade segment and axial flow fluid machine having the same
KR102182102B1 (en) * 2014-11-27 2020-11-23 한화에어로스페이스 주식회사 A turbine apparatus
FR3029962B1 (en) * 2014-12-11 2019-08-23 Safran Aircraft Engines AXIAL BLOCKING OF AUBES IN A TURBOMACHINE WHEEL
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
US10865646B2 (en) 2017-05-04 2020-12-15 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
US10774678B2 (en) 2017-05-04 2020-09-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
CN106958537B (en) * 2017-05-08 2023-06-06 珠海格力电器股份有限公司 Volute and air conditioner
US10458244B2 (en) * 2017-10-18 2019-10-29 United Technologies Corporation Tuned retention ring for rotor disk
FR3075284B1 (en) * 2017-12-18 2020-09-04 Safran Aircraft Engines SHOCK ABSORBER
US10738630B2 (en) 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
CN108917303B (en) * 2018-09-26 2023-02-24 珠海格力电器股份有限公司 Fan subassembly, fan and drying-machine
FR3106615B1 (en) * 2020-01-23 2021-12-31 Safran Aircraft Engines Turbomachine Kit
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 (en) * 2021-10-12 2023-04-14 Safran Aircraft Engines Upgraded turbomachine rotor
FR3127982A1 (en) * 2021-10-13 2023-04-14 Safran Aircraft Engines Movable ring assembly for turbomachine rotor
JP7414941B1 (en) * 2022-11-29 2024-01-16 株式会社東芝 Fixed structure of turbine rotor blades

Family Cites Families (10)

* 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 (en) * 1971-12-06 1973-03-30 Gen Electric BOLTLESS AUBA RETAINER FOR TURBOMACHIN ROTOR
FR2535794A1 (en) * 1982-11-08 1984-05-11 Snecma AXIAL AND RADIAL BLADE SUPPORT DEVICE
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
FR2663997B1 (en) * 1990-06-27 1993-12-24 Snecma DEVICE FOR FIXING A REVOLUTION CROWN ON A TURBOMACHINE DISC.
JPH08159281A (en) * 1994-12-07 1996-06-21 Nissan Diesel Motor Co Ltd Speed change mechanism for trasmission
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices
FR2803623B1 (en) * 2000-01-06 2002-03-01 Snecma Moteurs ARRANGEMENT FOR AXIAL RETENTION OF BLADES IN A DISC
FR2817289B1 (en) * 2000-11-30 2003-01-31 Snecma Moteurs DEVICE FOR CENTERING A TUBE IN A TURBINE SHAFT
US6951448B2 (en) * 2002-04-16 2005-10-04 United Technologies Corporation Axial retention system and components thereof for a bladed rotor

Also Published As

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

Similar Documents

Publication Publication Date Title
EP1746250B1 (en) Vibration damping elements for an axial holding ring of turbomachine fan blades
EP0110744B1 (en) Device for the radial and axial fixation of fan blades
EP1584784B1 (en) Assembly device for annular flanges, in particular in turbomachines
EP1584794B1 (en) Disk of a turbomachine rotor with an axial retention device for the blades
EP1873401B1 (en) Turbomachine rotor and turbomachine comprising such a rotor
EP0214875B1 (en) Damping element limiting the angular deflection of turbo machine rotor vanes
FR2973003A1 (en) SELF-ACTIVABLE LATCH FASTENING DEVICE
EP1760259B1 (en) Locking apparatus for an axial retention ring of a blade
EP2577091B1 (en) Angular damping device fitted with friction means which can be varied according to the rotation speed
FR2986836A1 (en) ANTI-WEAR ANNULAR TOOL FOR A TURBOMACHINE
FR2723397A1 (en) TURBOMACHINE COMPRESSOR DISK WITH ASYMMETRIC CIRCULAR GORGE
EP2053199B1 (en) Turbomachine wheel
EP2409044B1 (en) Disengageable axial abutment
FR2871538A1 (en) FRICTION DEVICE FOR A CLUTCH, IN PARTICULAR A MOTOR VEHICLE
FR2556427A1 (en) Locking ring for securing boss to spindle
EP2462361B1 (en) Prestressing device having radial activity
EP4263346A1 (en) Aircraft wheel braking device
FR2926613A1 (en) Blower disk for e.g. turbopropeller engine of airplane, has clamps at its external periphery, and bush authorizing pivotment of platform around rod of pin, where ends of bush is in support on head of pin and each clamp during tightening nut
WO1986004396A1 (en) Device having a centrifugal action particulary for clutch friction
EP3538788A1 (en) Mechanical transmission device
FR2503297A1 (en) Declutching stop for vehicle transmission - has shaft support blocked in rotation with respect to engagement control sleeve
FR2974142A1 (en) Immobilization device for ring used for retaining radial blade on disc of rotor of turboshaft engine, has stop including support face that is tilted relative to axial median plane of stop such that face is directed radially toward outside
FR2989992A1 (en) Device for immobilizing rotation of retention ring of blade on rotor disk of aircraft's engine, has ring whose portion is arranged such that edge is formed at bottom of groove of hook to avoid contact between upper edge of ring and bottom
EP2899415A1 (en) Rolling assembly including a rolling bearing unit and a mechanical part
FR2480378A1 (en) Diaphragm clutch for motor vehicle - uses jointing ring to clamp diaphragm to cover plate with ring and plate coupled by wedging forked tab in slot

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: NL

Payment date: 20230622

Year of fee payment: 18

Ref country code: FR

Payment date: 20230621

Year of fee payment: 18

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

Ref country code: DE

Payment date: 20230620

Year of fee payment: 18

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