EP0488874A1 - Fan rotor with blades without platforms and fillers reconstructing the streamline profile - Google Patents

Fan rotor with blades without platforms and fillers reconstructing the streamline profile Download PDF

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Publication number
EP0488874A1
EP0488874A1 EP91403182A EP91403182A EP0488874A1 EP 0488874 A1 EP0488874 A1 EP 0488874A1 EP 91403182 A EP91403182 A EP 91403182A EP 91403182 A EP91403182 A EP 91403182A EP 0488874 A1 EP0488874 A1 EP 0488874A1
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EP
European Patent Office
Prior art keywords
disc
shoe
shoes
wall
blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP91403182A
Other languages
German (de)
French (fr)
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EP0488874B1 (en
Inventor
Michel Antoine Brioude
Philippe Chereau
Jacky Naudet
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0488874A1 publication Critical patent/EP0488874A1/en
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Publication of EP0488874B1 publication Critical patent/EP0488874B1/en
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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
    • F04D29/26—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
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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 to a rotor of a blower or compressor stage of a turbomachine, of the type comprising a rotor disc, a series of radial blades mounted in axial housings produced in the periphery of said disc, a series of shoes disposed between said blades in order to maintain the spacing between said blades and to constitute the internal profile of the annular stream of fluid circulating from upstream to downstream of said stage, means for fixing said shoes on said disc and means for axially retaining said vanes in their respective housings, each of said shoes having an external wall defining the internal profile of the vein and remote from the periphery of said disc, the axial ends of said external wall being located substantially in the planes of the front and rear faces of said disc.
  • turbomachine rotor is particularly used in large diameter stages, because it is imperative, on the one hand, to limit the diameter of the disc carrying the blades because of the considerable centrifugal force obtained at high speeds of rotation of the turbomachine, and, on the other hand, to increase the internal diameter of the annular stream of fluid flowing from upstream to downstream of the stage so as to have a substantially uniform fluid flow speed throughout the section of the stream.
  • the British document GB-2 006 883 in particular shows a rotor for a turbomachine stage of the type mentioned above.
  • the shoe described in this document comprises, at the rear, an upwardly directed hook which cooperates with a groove provided in correspondence in a first retaining ring fixed by a bayonet device on the rear face of the disc, and it comprises, at the front, a rib which extends towards the axis of the disc and which cooperates with the front face of the disc to prevent the axial displacement of the shoe towards the back.
  • a second retaining ring, fixed by bolting, is provided on the front face of the disc to connect the front end of the shoe with said disc.
  • the shoe In this method of construction and attachment, the shoe must have an internal wall which is only partially supported on the periphery of the disc so that the rear hook can be engaged in the corresponding groove of the first retaining ring by pivoting. shoe on the periphery of the disc. This results in a complex configuration of the hoof and an increase in weight.
  • the bayonet device used to fix the first retaining ring on the rear face of the disc requires delicate machining of the disc and of this ring.
  • the object of the present invention is to overcome these drawbacks and to propose a turbomachine stage of the type mentioned in which the shoe has a simpler configuration and in which the means for fixing the shoes on the disc are different and easy to produce.
  • each of said shoes has a front wall and a rear wall which extend radially towards the axis of the turbomachine from said axial ends of the outer wall so as to cover at least partially the front and rear faces of said disc and, by the fact that the means for fixing said shoes to said disc comprise, for each of said shoes, at least one front hook extending axially towards the rear from its front wall and at minus a rear hook which extends forward from its rear wall, and grooves formed in said disc in correspondence with said hooks, said grooves extending between the ends of the mounting housings of the two blades adjacent to said shoe , said grooves and said hooks being shaped and dimensioned so that said shoe can be mounted by presentation to the right of a mounting housing and sliding of said shoe in the plane of the disc.
  • the grooves and the hooks cooperate with each other to retain the shoe radially during the rotation of the disc.
  • the front and rear walls of the shoe cooperate with the disc to axially retain the shoe forwards and backwards.
  • the grooves are preferably circular in shape, the center of which is on the axis of the turbomachine. But this is not compulsory. Their shape must allow the mounting of the shoe by sliding it in the plane of the disc.
  • each shoe has at least one cleat which extends from its rear wall to at least partially cover a mounting housing adjacent to said shoe and has a locking tab extending radially towards the axis of the turbomachine to from its front wall, said locking tab being spaced from the front face of said disc and cooperating with an additional groove of the disc, the axial retention means of said series of blades being formed, upstream of said stage, by said tabs and , downstream of said stage, by an annular segment interposed between the front face of said disc and said locking tabs.
  • each shoe also has a central partition which extends from its external wall towards the periphery of the disc and is substantially parallel to the plane of the adjacent blades, said partition having a slot in the vicinity of said external wall, and it is equipped with a vibration damper formed by a spring leaf passing through said slot and damping plates provided at the ends of said spring leaf.
  • each shoe also has additional walls extending from the underside of the external wall and serving as a stop for shock absorber pads.
  • the drawing shows a rotor 1 of a stage of a turbomachine, in which the blades 2 are fixed in axial housings 3 provided on the periphery 4 of a disc 5.
  • the blades 2 are of the type without platform.
  • the internal profile of the stream of fluid flowing upstream downstream of the blade stage is obtained by the external wall 6 of shoes 7 arranged between the blades 2 and fixed to the disc 5. Each shoe 7 also maintains the spacing between two adjacent blades 2.
  • each shoe 7 has a front wall 8 which extends radially towards the axis of the turbomachine from the front end 9 of the external wall 6 and which at least partially covers the front face 10 of the disc 5. It also has a rear wall 11 which extends radially towards the axis of the turbomachine from the rear end 12 of the external wall 6 and which at least partially covers the rear face 13 of the disc 5 .
  • the portions of the front 8 and rear 11 walls which cover the front 10 and rear 13 faces of the disc 5 have each at least one hook which extends axially towards the disc 5 and cooperates with a groove formed in correspondence in the wall of the disc 5.
  • the front wall 8 thus comprises at least one front hook 14 which extends towards the rear and cooperates with the groove 15, and the rear wall 11 has at least one hook 16 which extends forward and cooperates with the groove 17.
  • the front grooves 15 and rear 17 of the disc 5 extend between the axial housings 3 used for mounting the two blades 2 adjacent to the corresponding shoe 7.
  • the circumferential width of the hooks 14 and 16 must be less than the width of an axial housing 3 in line with the grooves 15 and 17 to allow the mounting of the stage vanes 1 as explained below.
  • the rear wall 11 of the shoe 7 is extended in the direction of the circumference of the disc 5 by at least one cleat 18 which at least partially closes the rear end of a mounting housing 3 adjacent to said shoe 7.
  • a stopper 18 is provided on each side of the shoe 7.
  • the shoe 7 also has on its front face a locking tab 19 which extends towards the axis of the turbomachine and which is spaced from the front face 10 of the disc 5. This locking tab 19 cooperates with an additional groove 20.
  • An annular segment 21 is interposed between the front face 10 of the disc 5 and all of the locking tabs 19 of the shoes 7.
  • the annular segment 21 at least partially covers the front ends housings 3 for mounting the blades 2.
  • the annular segment 21 and the tabs 18 of the shoes 7 thus constitute the means of axial retention of the blades 2.
  • Each shoe 7 also has on the underside of its outer wall 6 a central partition 22 which extends parallel to the adjacent vanes 2 towards the periphery 4 of the disc 5.
  • This central partition 22 has in the vicinity of the outer wall 6 a slot 23 through which passes a spring leaf 24 provided at each of its ends with damper plates 25.
  • the assembly 26 constituted by the spring leaf 24 and damper plates 25 constitutes a vibration damper.
  • the leaf spring 24 is of curvilinear shape, so that, when the rotor 1 stops, the plates 25 are in the vicinity of the periphery 4 of the disc 5. The action of the centrifugal force will force the plates 25 to move away from the periphery 4 of the disc 5 against the bending force of the spring leaf 24. The plates 25 then come to bear on the adjacent vanes 2 thus promoting vibration damping.
  • Each shoe 7 also has additional walls 27 which extend from the underside of the external wall 6 perpendicular to the central partition 22 and which serve as a stop for the plates 25.
  • the shoe 7 is made of a composite material.
  • the vibration damper 25 can be produced by mounting the damper plates 25 on the spring leaf 24, but it can also be produced in one piece, in which case it will be put in place when the composite shoe is manufactured. .
  • the blade 2 is mounted in a housing 3 by sliding it in a direction parallel to the axis of this housing 3; the shoe 7 is mounted by positioning its base in the housing 3 adjacent to the already mounted blade 2, by sliding it in the plane of the disc 5, the two hooks 14 and 16 being introduced into the corresponding grooves 15 and 17, and by pressing it against the already mounted blade 2.
  • the annular segment 21 is rotated between the front face 10 of the disc 5 and the locking tabs 19 after each assembly of a blade-shoe pair. We continue this assembly operation until the last dawn 2.

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

Abstract

The present invention relates to a fan rotor (1) comprising a disc (5), radial vanes (2) mounted in axial housings (3) produced in the periphery (4) of the disc (5) and fillers (7) interposed between the vanes (2) in order to reconstruct the streamline profile. The fillers have an outer wall and front and rear walls each comprising at least one hook, the said hooks interacting with grooves provided in the front and rear faces of the disc. The filler (7) further comprises a median partition (22) fitted with a slot (23) for the passage of a spring blade of a vibration damper. <IMAGE>

Description

La présente invention concerne un rotor d'un étage de soufflante ou de compresseur d'une turbomachine, du type comportant un disque de rotor, une série d'aubes radiales montées dans des logements axiaux réalisés dans la périphérie dudit disque, une série de sabots disposés entre lesdites aubes afin de maintenir l'écartement entre lesdites aubes et de constituer le profil interne de la veine annulaire de fluide circulant d'amont en aval dudit étage, des moyens de fixation desdits sabots sur ledit disque et des moyens de rétention axiale desdites aubes dans leurs logements respectifs, chacun desdits sabots présentant une paroi externe délimitant le profil interne de la veine et éloignée de la périphérie dudit disque, les extrémités axiales de ladite paroi externe étant situées sensiblement dans les plans des faces avant et arrière dudit disque.The present invention relates to a rotor of a blower or compressor stage of a turbomachine, of the type comprising a rotor disc, a series of radial blades mounted in axial housings produced in the periphery of said disc, a series of shoes disposed between said blades in order to maintain the spacing between said blades and to constitute the internal profile of the annular stream of fluid circulating from upstream to downstream of said stage, means for fixing said shoes on said disc and means for axially retaining said vanes in their respective housings, each of said shoes having an external wall defining the internal profile of the vein and remote from the periphery of said disc, the axial ends of said external wall being located substantially in the planes of the front and rear faces of said disc.

Ce type de rotor de turbomachine est particulièrement utilisé dans les étages de grand diamètre, car il est impératif, d'une part, de limiter le diamètre du disque portant les aubes à cause de la force centrifuge considérable obtenues aux grandes vitesses de rotation de la turbomachine, et, d'autre part, d'augmenter le diamètre interne de la veine annulaire de fluide circulant d'amont en aval de l'étage pour avoir une vitesse d'écoulement de fluide sensiblement uniforme dans toute la section de la veine.This type of turbomachine rotor is particularly used in large diameter stages, because it is imperative, on the one hand, to limit the diameter of the disc carrying the blades because of the considerable centrifugal force obtained at high speeds of rotation of the turbomachine, and, on the other hand, to increase the internal diameter of the annular stream of fluid flowing from upstream to downstream of the stage so as to have a substantially uniform fluid flow speed throughout the section of the stream.

Dans le cas d'aubes de petite dimension il est courant d'utiliser des aubes avec plates-formes. Mais lorsque les aubes sont de grande dimension cette façon de faire n'est pas souhaitable car elle entraîne une augmentation substantielle du poids des pieds d'aube.In the case of small blades it is common to use blades with platforms. But when the blades are large this way of doing things is not desirable because it results in a substantial increase in the weight of the blade roots.

Le document britannique GB-2 006 883 en particulier montre un rotor pour un étage de turbomachine du type mentionné ci-dessus. Le sabot décrit dans ce document comporte, à l'arrière, un crochet dirigé vers le haut qui coopère avec une rainure prévue en correspondance dans un premier anneau de retenue fixé par un dispositif à baïonnette sur la face arrière du disque, et il comporte, à l'avant, une nervure qui s'étend vers l'axe du disque et qui coopère avec la face avant du disque pour empêcher le déplacement axial du sabot vers l'arrière. Un deuxième anneau de retenue, fixé par boulonnage, est prévu sur la face avant du disque pour relier l'extrémité avant du sabot avec ledit disque.The British document GB-2 006 883 in particular shows a rotor for a turbomachine stage of the type mentioned above. The shoe described in this document comprises, at the rear, an upwardly directed hook which cooperates with a groove provided in correspondence in a first retaining ring fixed by a bayonet device on the rear face of the disc, and it comprises, at the front, a rib which extends towards the axis of the disc and which cooperates with the front face of the disc to prevent the axial displacement of the shoe towards the back. A second retaining ring, fixed by bolting, is provided on the front face of the disc to connect the front end of the shoe with said disc.

Dans ce mode de construction et de fixation il est nécessaire que le sabot présente une paroi interne qui n'est que partiellement en appui sur le pourtour du disque de manière à pouvoir engager le crochet arrière dans la rainure correspondante du premier anneau de retenue par pivotement du sabot sur la périphérie du disque. Ceci se traduit par une configuration complexe du sabot et une augmentation de poids. De plus le dispositif à baïonnette servant à fixer le premier anneau de retenue sur la face arrière du disque demande un usinage délicat du disque et de cet anneau.In this method of construction and attachment, the shoe must have an internal wall which is only partially supported on the periphery of the disc so that the rear hook can be engaged in the corresponding groove of the first retaining ring by pivoting. shoe on the periphery of the disc. This results in a complex configuration of the hoof and an increase in weight. In addition, the bayonet device used to fix the first retaining ring on the rear face of the disc requires delicate machining of the disc and of this ring.

Le but de la présente invention est de pallier ces inconvénients et de proposer un étage de turbomachine du type mentionné dans lequel le sabot ait une configuration plus simple et dans lequel les moyens de fixation des sabots sur le disque sont différents et faciles à réaliser.The object of the present invention is to overcome these drawbacks and to propose a turbomachine stage of the type mentioned in which the shoe has a simpler configuration and in which the means for fixing the shoes on the disc are different and easy to produce.

Le but est atteint selon l'invention par le fait que chacun desdits sabots comporte une paroi avant et une paroi arrière qui s'étendent radialement vers l'axe de la turbomachine à partir desdites extrémités axiales de paroi externe de manière à recouvrir au moins partiellement les faces avant et arrière dudit disque et, par le fait que les moyens de fixation desdits sabots sur ledit disque comportent, pour chacun desdits sabots, au moins un crochet avant s'étendant axialement vers l'arrière à partir de sa paroi avant et au moins un crochet arrière qui s'étend vers l'avant à partir de sa paroi arrière, et des gorges ménagées dans ledit disque en correspondance avec lesdits crochets, lesdites gorges s'étendant entre les extrémités des logements de montage des deux aubes adjacentes audit sabot, lesdites gorges et lesdits crochets étant conformés et dimensionnés pour que ledit sabot puisse être monté par présentation au droit d'un logement de montage et glissement dudit sabot dans le plan du disque.The object is achieved according to the invention by the fact that each of said shoes has a front wall and a rear wall which extend radially towards the axis of the turbomachine from said axial ends of the outer wall so as to cover at least partially the front and rear faces of said disc and, by the fact that the means for fixing said shoes to said disc comprise, for each of said shoes, at least one front hook extending axially towards the rear from its front wall and at minus a rear hook which extends forward from its rear wall, and grooves formed in said disc in correspondence with said hooks, said grooves extending between the ends of the mounting housings of the two blades adjacent to said shoe , said grooves and said hooks being shaped and dimensioned so that said shoe can be mounted by presentation to the right of a mounting housing and sliding of said shoe in the plane of the disc.

Les gorges et les crochets coopèrent entre eux pour retenir radialement le sabot lors de la rotation du disque. Les parois avant et arrière du sabot coopèrent avec le disque pour retenir axialement le sabot vers l'avant et vers l'arrière. Les gorges ont une forme de préférence circulaire dont le centre se trouve sur l'axe de la turbomachine. Mais ceci n'est pas obligatoire. Leur forme doit permettre le montage du sabot en faisant glisser ce dernier dans le plan du disque.The grooves and the hooks cooperate with each other to retain the shoe radially during the rotation of the disc. The front and rear walls of the shoe cooperate with the disc to axially retain the shoe forwards and backwards. The grooves are preferably circular in shape, the center of which is on the axis of the turbomachine. But this is not compulsory. Their shape must allow the mounting of the shoe by sliding it in the plane of the disc.

Le montage des sabots se fait ainsi sans boulonnage. Le dispositif à baïonnette de l'art antérieur est supprimé et l'usinage du disque de rotor est simplifié.The mounting of the shoes is thus done without bolting. The bayonet device of the prior art is eliminated and the machining of the rotor disc is simplified.

Avantageusement, chaque sabot présente au moins un taquet qui s'étend à partir de sa paroi arrière pour venir recouvrir au moins partiellement un logement de montage adjacent audit sabot et présente une patte de verrouillage s'étendant radialement vers l'axe de la turbomachine à partir de sa paroi avant, ladite patte de verrouillage étant espacée de la face avant dudit disque et coopérant avec une gorge supplémentaire du disque, les moyens de rétention axiale de ladite série d'aubes étant consistués, en amont dudit étage, par lesdits taquets et, en aval dudit étage, par un segment annulaire interposé entre la face avant dudit disque et lesdites pattes de verrouillage.Advantageously, each shoe has at least one cleat which extends from its rear wall to at least partially cover a mounting housing adjacent to said shoe and has a locking tab extending radially towards the axis of the turbomachine to from its front wall, said locking tab being spaced from the front face of said disc and cooperating with an additional groove of the disc, the axial retention means of said series of blades being formed, upstream of said stage, by said tabs and , downstream of said stage, by an annular segment interposed between the front face of said disc and said locking tabs.

Avantageusement, chaque sabot présente de plus une cloison médiane qui s'étend à partir de sa paroi externe vers la périphérie du disque et est sensiblement parallèle au plan des aubes adjacentes, ladite cloison présentant une fente au voisinage de ladite paroi externe, et il est équipé d'un amortisseur de vibrations formé d'une lame de ressort passant par ladite fente et de plaquettes d'amortissement prévues aux extrémités de ladite lame de ressort.Advantageously, each shoe also has a central partition which extends from its external wall towards the periphery of the disc and is substantially parallel to the plane of the adjacent blades, said partition having a slot in the vicinity of said external wall, and it is equipped with a vibration damper formed by a spring leaf passing through said slot and damping plates provided at the ends of said spring leaf.

Avantageusement chaque sabot comporte de plus des parois supplémentaires s'étendant à partir de la face inférieure de la paroi externe et servant de butée pour plaquettes d'amortisseur.Advantageously, each shoe also has additional walls extending from the underside of the external wall and serving as a stop for shock absorber pads.

D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence au dessin annexé dans lequel :

  • la figure 1 est une coupe du rotor d'un étage d'aubes de turbomachine selon un plan passant par l'axe de la turbomachine et équidistant de deux aubes adjacentes,
  • la figure 2 est une coupe selon un plan perpendiculaire à l'axe de la turbomachine et selon la ligne II-II de la figure 1,
  • la figure 3 est une vue de dessous et en perspective d'un sabot équipé d'un dispositif amortisseur de vibrations,
  • la figure 4 est une vue de dessus et en perspective d'un sabot,
  • la figure 5 est une vue en perspective d'un dispositif amortisseur de vibrations,
  • la figure 6 est une vue latérale du rotor, montrant le montage de la dernière aube, et
  • la figure 7 est une vue frontale du rotor avant le montage de la dernière aube.
Other characteristics and advantages of the invention will emerge on reading the following description given by way of example and with reference to the appended drawing in which:
  • FIG. 1 is a section through the rotor of a stage of turbomachine blades along a plane passing through the axis of the turbomachine and equidistant from two adjacent blades,
  • FIG. 2 is a section on a plane perpendicular to the axis of the turbomachine and on line II-II of FIG. 1,
  • FIG. 3 is a view from below and in perspective of a shoe fitted with a vibration damping device,
  • FIG. 4 is a top view and in perspective of a shoe,
  • FIG. 5 is a perspective view of a vibration damping device,
  • FIG. 6 is a side view of the rotor, showing the mounting of the last blade, and
  • Figure 7 is a front view of the rotor before mounting the last blade.

Le dessin montre un rotor 1 d'un étage d'une turbomachine, dans lequel les aubes 2 sont fixées dans des logements axiaux 3 prévus sur la périphérie 4 d'un disque 5. Les aubes 2 sont du type sans plate-forme. Le profil interne de la veine de fluide circulant d'amont en aval de l'étage d'aubes est obtenu par la paroi externe 6 de sabots 7 disposés entre les aubes 2 et fixés au disque 5. Chaque sabot 7 maintient de plus l'écartement entre deux aubes adjacentes 2.The drawing shows a rotor 1 of a stage of a turbomachine, in which the blades 2 are fixed in axial housings 3 provided on the periphery 4 of a disc 5. The blades 2 are of the type without platform. The internal profile of the stream of fluid flowing upstream downstream of the blade stage is obtained by the external wall 6 of shoes 7 arranged between the blades 2 and fixed to the disc 5. Each shoe 7 also maintains the spacing between two adjacent blades 2.

Selon l'invention, chaque sabot 7 présente une paroi avant 8 qui s'étend radialement vers l'axe de la turbomachine à partir de l'extrémité avant 9 de la paroi externe 6 et qui vient recouvrir au moins partiellement la face avant 10 du disque 5. Il présente de plus une paroi arrière 11 qui s'étend radialement vers l'axe de la turbomachine à partir de l'extrémité arrière 12 de la paroi externe 6 et qui vient recouvrir au moins partiellement la face arrière 13 du disque 5.According to the invention, each shoe 7 has a front wall 8 which extends radially towards the axis of the turbomachine from the front end 9 of the external wall 6 and which at least partially covers the front face 10 of the disc 5. It also has a rear wall 11 which extends radially towards the axis of the turbomachine from the rear end 12 of the external wall 6 and which at least partially covers the rear face 13 of the disc 5 .

Les portions des parois avant 8 et arrière 11 qui recouvrent les faces avant 10 et arrière 13 du disque 5 présentent chacune au moins un crochet qui s'étend axialement vers le disque 5 et coopère avec une gorge formée en correspondance dans la paroi du disque 5. La paroi avant 8 comporte ainsi au moins un crochet avant 14 qui s'étend vers l'arrière et coopère avec la gorge 15, et la paroi arrière 11 présente au moins un crochet 16 qui s'étend vers l'avant et coopère avec la gorge 17. Les gorges avant 15 et arrière 17 du disque 5 s'étendent entre les logements axiaux 3 servant au montage des deux aubes 2 voisines du sabot correspondant 7. La largeur circonférentielle des crochets 14 et 16 doit être inférieure à la largeur d'un logement axial 3 au droit des gorges 15 et 17 pour permettre le montage de l'étage d'aubes 1 comme cela est expliqué plus loin.The portions of the front 8 and rear 11 walls which cover the front 10 and rear 13 faces of the disc 5 have each at least one hook which extends axially towards the disc 5 and cooperates with a groove formed in correspondence in the wall of the disc 5. The front wall 8 thus comprises at least one front hook 14 which extends towards the rear and cooperates with the groove 15, and the rear wall 11 has at least one hook 16 which extends forward and cooperates with the groove 17. The front grooves 15 and rear 17 of the disc 5 extend between the axial housings 3 used for mounting the two blades 2 adjacent to the corresponding shoe 7. The circumferential width of the hooks 14 and 16 must be less than the width of an axial housing 3 in line with the grooves 15 and 17 to allow the mounting of the stage vanes 1 as explained below.

La paroi arrière 11 du sabot 7 est prolongée dans le sens de la circonférence du disque 5 par au moins un taquet 18 qui vient obturer au moins partiellement l'extrémité arrière d'un logement de montage 3 adjacent audit sabot 7. De préférence il est prévu un taquet 18 de chaque côté du sabot 7. Le sabot 7 présente de plus sur sa face avant une patte de verrouillage 19 qui s'étend vers l'axe de la turbomachine et qui est écartée de la face avant 10 du disque 5. Cette patte de verrouillage 19 coopère avec une gorge supplémentaire 20. Un segment annulaire 21 est interposé entre la face avant 10 du disque 5 et l'ensemble des pattes de verrouillage 19 des sabots 7. Le segment annulaire 21 recouvre au moins partiellement les extrémités avant des logements 3 de montage des aubes 2. Le segment annulaire 21 et les taquets 18 des sabots 7 constituent ainsi les moyens de rétention axiale des aubes 2.The rear wall 11 of the shoe 7 is extended in the direction of the circumference of the disc 5 by at least one cleat 18 which at least partially closes the rear end of a mounting housing 3 adjacent to said shoe 7. Preferably it is a stopper 18 is provided on each side of the shoe 7. The shoe 7 also has on its front face a locking tab 19 which extends towards the axis of the turbomachine and which is spaced from the front face 10 of the disc 5. This locking tab 19 cooperates with an additional groove 20. An annular segment 21 is interposed between the front face 10 of the disc 5 and all of the locking tabs 19 of the shoes 7. The annular segment 21 at least partially covers the front ends housings 3 for mounting the blades 2. The annular segment 21 and the tabs 18 of the shoes 7 thus constitute the means of axial retention of the blades 2.

Chaque sabot 7 présente de plus sur la face inférieure de sa paroi externe 6 une cloison médiane 22 qui s'étend parallèlement aux aubes adjacentes 2 vers la périphérie 4 du disque 5. Cette cloison médiane 22 présente au voisinage de la paroi externe 6 une fente 23 dans laquelle passe une lame de ressort 24 munie à chacune de ses extrémités de plaquettes d'amortisseur 25. L'ensemble 26 constitué par la lame de ressort 24 et des plaquettes d'amortisseur 25 constitue un amortisseur de vibrations. La lame de ressort 24 est de forme curviligne, de telle manière que, à l'arrêt du rotor 1, les plaquettes 25 se trouvent au voisinage de la périphérie 4 du disque 5. L'action de la force centrifuge forcera les plaquettes 25 à s'éloigner de la périphérie 4 du disque 5 à l'encontre de la force de flexion de la lame à ressort 24. Les plaquettes 25 viennent alors s'appuyer sur les aubes adjacentes 2 favorisant ainsi l'amortissement vibratoire. Chaque sabot 7 présente de plus des parois supplémentaires 27 qui s'étendent à partir de la face inférieure de la paroi externe 6 perpendiculairement à la cloison médiane 22 et qui servent de butée aux plaquettes 25.Each shoe 7 also has on the underside of its outer wall 6 a central partition 22 which extends parallel to the adjacent vanes 2 towards the periphery 4 of the disc 5. This central partition 22 has in the vicinity of the outer wall 6 a slot 23 through which passes a spring leaf 24 provided at each of its ends with damper plates 25. The assembly 26 constituted by the spring leaf 24 and damper plates 25 constitutes a vibration damper. The leaf spring 24 is of curvilinear shape, so that, when the rotor 1 stops, the plates 25 are in the vicinity of the periphery 4 of the disc 5. The action of the centrifugal force will force the plates 25 to move away from the periphery 4 of the disc 5 against the bending force of the spring leaf 24. The plates 25 then come to bear on the adjacent vanes 2 thus promoting vibration damping. Each shoe 7 also has additional walls 27 which extend from the underside of the external wall 6 perpendicular to the central partition 22 and which serve as a stop for the plates 25.

Le sabot 7 est réalisé dans un matériau composite. L'amortisseur de vibrations 25 peut être réalisé par montage des plaquettes d'amortisseur 25 sur la lame de ressort 24, mais il peut également être réalisé en une seule pièce auquel cas il sera mis en place au moment de la fabrication du sabot en composite.The shoe 7 is made of a composite material. The vibration damper 25 can be produced by mounting the damper plates 25 on the spring leaf 24, but it can also be produced in one piece, in which case it will be put in place when the composite shoe is manufactured. .

Le montage d'une aube 2 et d'un sabot 7 adjacent sur le disque 5 se fait de la façon suivante :The mounting of a blade 2 and a shoe 7 adjacent to the disc 5 is done as follows:

l'aube 2 est montée dans un logement 3 en la faisant glisser selon une direction parallèle à l'axe de ce logement 3 ; le sabot 7 est monté en positionnant sa base dans le logement 3 voisin de l'aube 2 déjà montée, en le faisant glisser dans le plan du disque 5, les deux crochets 14 et 16 s'introduisant dans les gorges correspondantes 15 et 17, et en le plaquant contre l'aube 2 déjà montée. On fait tourner le segment annulaire 21 entre la face avant 10 du disque 5 et les pattes de verrouillage 19 après chaque montage d'un couple aube-sabot. On continue cette opération de montage jusqu'à la dernière aube 2.the blade 2 is mounted in a housing 3 by sliding it in a direction parallel to the axis of this housing 3; the shoe 7 is mounted by positioning its base in the housing 3 adjacent to the already mounted blade 2, by sliding it in the plane of the disc 5, the two hooks 14 and 16 being introduced into the corresponding grooves 15 and 17, and by pressing it against the already mounted blade 2. The annular segment 21 is rotated between the front face 10 of the disc 5 and the locking tabs 19 after each assembly of a blade-shoe pair. We continue this assembly operation until the last dawn 2.

Pour monter la dernière aube 2′, on procède comme représenté sur les figures 6 et 7. On positionne d'abord les deux sabots 7′ et 7˝ voisins du logement 3′ de la dernière aube, après avoir pris soin de faire passer l'extrémité 27 du segment annulaire 21 au-dessus des taquets de verrouillage 19 correspondants pour permettre le dégagement de l'extrémité avant du logement axial 3′, puis on glisse le pied de l'aube 2′, dans le logement 3′. Les taquets 18 voisins des deux sabots 7′ et 7˝ sont évidemment dimensionnés pour qu'il soit possible de présenter le dernier sabot 7˝ dans le logement 3′ lorsque le sabot 7′ est correctement positionné. Ensuite on fait tourner le segment annulaire 21 dans le sens approprié pour que son extrémité 27 soit interposée entre le disque 5 et les taquets de verrouillage 19.To assemble the last blade 2 ′, proceed as shown in FIGS. 6 and 7. First, position the two shoes 7 ′ and 7˝ adjacent to the housing 3 ′ of the last blade, after having taken care to pass the 'end 27 of the annular segment 21 above the corresponding locking tabs 19 to allow the release of the front end of the axial housing 3 ′, then the foot of the blade 2 ′ is slid into the housing 3 ′. The cleats 18 next to the two shoes 7 ′ and 7˝ are obviously dimensioned so that it is possible to present the last shoe 7˝ in the housing 3 ′ when the shoe 7 ′ is correctly positioned. Then the annular segment 21 is rotated in the appropriate direction so that its end 27 is interposed between the disc 5 and the locking tabs 19.

Claims (4)

Rotor d'un étage de soufflante ou de compresseur d'une turbomachine, du type comportant un disque de rotor (5), une série d'aubes (2) radiales montées dans des logements axiaux (3) réalisés dans la périphérie (4) dudit disque (5), une série de sabots (7) disposés entre lesdites aubes (2) afin de maintenir l'écartement entre lesdites aubes (2) et de constituer le profil interne de la veine de fluide circulant d'amont en aval dudit étage, des moyens de fixation desdits sabots (7) sur ledit disque (5) et des moyens de rétention axiales desdites aubes (2) dans leurs logements (3) respectifs,
   chacun desdits sabots (7) présentant une paroi externe (6) délimitant le profil interne de la veine et éloignée de la périphérie (4) dudit disque (5),
   les extrémités axiales (9, 12) desdits sabots (7) étant situées sensiblement et respectivement dans les plans des faces avant (10) et arrière (13) dudit disque (5),
   caractérisé en ce que chacun desdits sabots (7) comporte une paroi avant (8) et une paroi arrière (11) qui s'étendent radialement vers l'axe de la turbomachine à partir desdites extrémités axiales (9, 12) de la paroi externe de manière à recouvrir au moins partiellement les faces avant (10) et arrière (13) dudit disque, et en ce que les moyens de fixation desdits sabots (7) sur ledit disque (5) comportent, pour chacun desdits sabots (7), au moins un crochet avant (14) s'étendant axialement vers l'arrière à partir de sa paroi avant (8), au moins un crochet arrière (16) s'étendant axialement vers l'avant à partir de sa paroi arrière (11), et de gorges (15, 17) ménagées dans ledit disque (5) en correspondance avec lesdits crochets (14, 16), lesdites gorges (15, 17) s'étendant entre les extrémités des logements de montage (3) des deux aubes (2) adjacentes audit sabot (7), lesdites gorges (15, 17) et lesdits crochets (14, 16) étant conformés et dimensionnés pour que ledit sabot (7) puisse être monté par présentation au droit d'un logement de montage (3) et glissement dudit sabot (7) dans le plan dudit disque (5).Rotor of a fan or compressor stage of a turbomachine, of the type comprising a rotor disc (5), a series of radial vanes (2) mounted in axial housings (3) produced in the periphery (4) of said disc (5), a series of shoes (7) disposed between said vanes (2) in order to maintain the spacing between said vanes (2) and to constitute the internal profile of the stream of fluid circulating from upstream to downstream of said stage, means for fixing said shoes (7) to said disc (5) and means for axial retention of said blades (2) in their respective housings (3),
each of said shoes (7) having an external wall (6) delimiting the internal profile of the vein and distant from the periphery (4) of said disc (5),
the axial ends (9, 12) of said shoes (7) being located substantially and respectively in the planes of the front (10) and rear (13) faces of said disc (5),
characterized in that each of said shoes (7) has a front wall (8) and a rear wall (11) which extend radially towards the axis of the turbomachine from said axial ends (9, 12) of the external wall so as to at least partially cover the front (10) and rear (13) faces of said disc, and in that the means for fixing said shoes (7) to said disc (5) comprise, for each of said shoes (7), at least one front hook (14) extending axially rearward from its front wall (8), at least one rear hook (16) extending axially forward from its rear wall (11 ), and grooves (15, 17) formed in said disc (5) in correspondence with said hooks (14, 16), said grooves (15, 17) extending between the ends of the mounting housings (3) of the two vanes (2) adjacent to said shoe (7), said grooves (15, 17) and said hooks (14, 16) being shaped and dimensioned so that said shoe (7) can be mounted by presentation to the right of a mounting housing (3) and sliding of said shoe (7) in the plane of said disc (5). Rotor selon la revendication 1, caractérisé en ce que chaque sabot (7) présente au moins un taquet (18) qui s'étend à partir de sa paroi arrière (11) et vient recouvrir au moins partiellement un logement de montage (3) adjacent audit sabot (7), et une patte de verrouillage (19) s'étendant radialement vers l'axe de la turbomachine à partir de sa paroi avant (8), ladite patte de verrouillage (19) étant écartée de la face avant (10) dudit disque (5) et coopérant avec une gorge supplémentaire (20) du disque (5), et
   en ce que les moyens de rétention axiale de ladite série d'aubes (2) sont constitués, en amont dudit étage, par lesdits taquets (18) et, en aval dudit étage, par un segment annulaire (21) interposé entre la face avant (10) dudit disque (5) et lesdites pattes de verrouillage (19).Rotor according to claim 1, characterized in that each shoe (7) has at least one cleat (18) which extends from its rear wall (11) and at least partially covers an adjacent mounting housing (3) said shoe (7), and a locking tab (19) extending radially towards the axis of the turbomachine from its front wall (8), said locking tab (19) being spaced from the front face (10 ) of said disc (5) and cooperating with an additional groove (20) of the disc (5), and
in that the axial retention means of said series of blades (2) are constituted, upstream of said stage, by said cleats (18) and, downstream of said stage, by an annular segment (21) interposed between the front face (10) of said disc (5) and said locking tabs (19). Etage selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que chaque sabot (7) présente de plus une cloison médiane (22) qui s'étend à partir de sa paroi externe (6) vers la périphérie (4) du disque (5) et est sensiblement parallèle au plan des aubes adjacentes (2), ladite cloison (22) présentant une fente (23) au voisinage de ladite paroi externe (6), et en ce qu'il est équipé d'un amortisseur de vibrations (26) formé d'une lame de ressort (24) passant par ladite fente (23) et de plaquettes d'amortisseur (25) prévues aux extrémités de ladite lame de ressort (24).Stage according to either of Claims 1 and 2, characterized in that each shoe (7) also has a central partition (22) which extends from its external wall (6) towards the periphery (4) of the disc (5) and is substantially parallel to the plane of the adjacent blades (2), said partition (22) having a slot (23) in the vicinity of said outer wall (6), and in that it is equipped with a damper vibration (26) formed of a spring leaf (24) passing through said slot (23) and damper plates (25) provided at the ends of said spring leaf (24). Etage selon la revendication 3, caractérisé en ce que chaque sabot (7) comporte en plus des parois supplémentaires (27) s'étendant à partir de la face inférieure de sa paroi externe (6) et servant de butée pour les plaquettes d'amortisseur (25).Stage according to claim 3, characterized in that each shoe (7) further comprises additional walls (27) extending from the underside of its external wall (6) and serving as a stop for the shock absorber pads (25).
EP91403182A 1990-11-28 1991-11-26 Fan rotor with blades without platforms and fillers reconstructing the streamline profile Expired - Lifetime EP0488874B1 (en)

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FR909014850A FR2669686B1 (en) 1990-11-28 1990-11-28 BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
FR9014850 1990-11-28

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EP0488874A1 true EP0488874A1 (en) 1992-06-03
EP0488874B1 EP0488874B1 (en) 1994-11-09

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EP (1) EP0488874B1 (en)
DE (1) DE69105099T2 (en)
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WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US5466125A (en) * 1992-04-16 1995-11-14 Rolls-Royce Plc Rotors for gas turbine engines
FR2716502A1 (en) * 1994-02-23 1995-08-25 Snecma Sealing between vanes and intermediate platforms.
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FR3003294A1 (en) * 2013-03-15 2014-09-19 Snecma MULTI-FLOW TURBOMOTEUR BLOWER, AND TURBOMOTEUR EQUIPPED WITH SUCH BLOWER
GB2526475A (en) * 2013-03-15 2015-11-25 Snecma Multiflow turbojet engine fan and turbojet engine fitted with such a fan
GB2526475B (en) * 2013-03-15 2018-05-16 Snecma Fan for a multi-flow turboshaft engine, and turboshaft engine equipped with such a fan

Also Published As

Publication number Publication date
FR2669686A1 (en) 1992-05-29
US5161949A (en) 1992-11-10
DE69105099T2 (en) 1995-04-20
EP0488874B1 (en) 1994-11-09
DE69105099D1 (en) 1994-12-15
FR2669686B1 (en) 1994-09-02

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