EP1496266A1 - Connection between rotor disks in a compressor - Google Patents

Connection between rotor disks in a compressor Download PDF

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Publication number
EP1496266A1
EP1496266A1 EP04291706A EP04291706A EP1496266A1 EP 1496266 A1 EP1496266 A1 EP 1496266A1 EP 04291706 A EP04291706 A EP 04291706A EP 04291706 A EP04291706 A EP 04291706A EP 1496266 A1 EP1496266 A1 EP 1496266A1
Authority
EP
European Patent Office
Prior art keywords
ring
rotor
holes
disk
piece
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
EP04291706A
Other languages
German (de)
French (fr)
Other versions
EP1496266B1 (en
Inventor
Didier René André Escure
Gérard Gabriel Miraucourt
Francis Gilles Basile Soniak
Erick Jacques Boston
Jacques Robert Audet
Marie-France Bourgeois
Daniel Dao
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 Moteurs SA
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 Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1496266A1 publication Critical patent/EP1496266A1/en
Application granted granted Critical
Publication of EP1496266B1 publication Critical patent/EP1496266B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49721—Repairing with disassembling
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49947—Assembling or joining by applying separate fastener
    • Y10T29/49948—Multipart cooperating fastener [e.g., bolt and nut]

Definitions

  • the invention relates to the field of high-pressure turbojet compressors, and more particularly that of the connection between the bladed disk of the first stage of the rotor of the compressor and the bladed disc of the second stage of the compressor rotor.
  • the compressor receives the inlet air flow.
  • the disc bladed at the compressor inlet is likely to receive foreign bodies such as ice cubes, birds or others.
  • the first is thus most exposed to damage by foreign bodies. Because of this, it is also the one that requires maintenance operations that may require disassembly of the blisk. Any disassembly of the rotor line of the compressor including different parts leads to balancing and alignment operations that require a transition to qualified and equipped maintenance workshop. During these dismantling operations, it is important that the rotor line is not broken.
  • a solution has been proposed in EP 1122 443 where a monobloc blisk (DAM) is used as the first blisk of the compressor.
  • DAM monobloc blisk
  • This blisk is fixed by a upstream flange at the compressor inlet.
  • this solution does not bring complete satisfaction because it does not allow to meet certain criteria relating to the blisk. for example a vibration resistance criterion, a lifetime criterion, or a criterion of held at the loss of blades.
  • the present invention improves the situation.
  • the invention relates to a part for attachment to the inlet of a compressor rotor, this piece being able to constitute a first part of a compressor rotor.
  • the piece is terminated by a first ring with a succession of holes and notches.
  • the axis of the first ring is adapted to be centered on the axis of rotation of the compressor rotor for attachment to the rotor inlet of compressor, the first ring is able to be placed against a second symmetry piece rotor revolution fixed to a third rotor symmetry piece by fastening means and forming a set second / third rotor parts, the notches being able to bypass the fastening means of the set second / third parts of the rotor, the holes of the first ring being able to be placed opposite the holes of the assembly second / third pieces for fixing the first ring to the second / third set rooms.
  • the first ring is in a plane perpendicular to the axis of rotation of the rotor.
  • the part comprises a disc and blades attached on its periphery.
  • the part comprises a disk provided with a flange connected to the first ring, the flange and the ring being placed downstream of the disc so that the attachment of the disc with the assembly second / third parts can be performed downstream of the disc relative to the direction Flow flow in the compressor.
  • the invention also relates to a connection between a first piece as defined previously, terminated by a first ring provided with a succession of holes and of notches, the axis of the first ring being centered on the axis of rotation of the rotor of compressor for attachment to the compressor rotor inlet, and a set of a second rotor piece attached to a third rotor piece, the second piece forming the input of the compressor rotor and being terminated downstream by a second ring comprising holes, the third piece being terminated upstream by a third ring comprising holes, the second and third rings being arranged one against the other, so as to place their holes facing each other, and being fixed between them by first means fixing, the first circular ring being disposed upstream of and against the assembly second / third pieces so that the notches circumvent the first means securing the second / third rotor assembly and that at least some holes of the first ring are opposite holes of the set second / third parts, second fixing means fixing the first circular ring to the assembly second
  • the second and third rings are in a plane perpendicular to the axis of rotation of the rotor.
  • the fastening means of the assembly of second / third rotor parts are shorter than the fixing means for fixing the first ring to the whole second / third pieces.
  • fastening means comprise screw-nut systems.
  • the screw of the screw-nut system is retained by a ring allowing the screw to hold in case of absence of the nut.
  • the invention relates in particular to a turbomachine comprising a high-pressure compressor provided with a link as described above.
  • the invention further relates to a method of mounting a link as described previously, of placing the second and third circular rings one against the other, so as to place their holes opposite, to fix these second and third rings between them by first fixing means passing through some of the holes, to be placed in the remaining holes of the second fixing means capable of fixing the second / third assembly piece to the first piece, to place the first circular ring upstream of and against the whole second / third piece so that the notches circumvent the means fixing the entire second / third rotor parts and that some of the holes the first ring are traversed by the second fastening means in order to fix the first circular ring to the second / third pieces set.
  • the invention further relates to a method of disassembling a link as described previously, of undoing the second fastening means to remove the first compressor rotor part and keep the whole second piece / third piece of the rotor.
  • FIG. 1 represents a partial section of the rotor part of a high-pressure compressor turbojet engine composed of different stages of compression E1 to E5, each comprising a disk D1 to D5 provided with a blade ring A1 to A5.
  • Each compression stage is also composed, downstream of each blisk, of a not shown flow rectifier and forming part of the stator part of the compressor. Each rectifier straighten the airflow before entering the next compression stage.
  • the rotor part and the part compressor stator delimit a "vein" for the airflow to be compressed. We are talking about rotor line to denote the continuous outer surface of the rotor forming the lower limit of this vein.
  • the bladed discs D2 to D5 of the compressor are formed in one piece called set of disks.
  • the bladed disk D1 is advantageously a blisk. monobloc attached to the rotor upstream of the set of discs to be easily disassembled for maintenance and servicing.
  • This first blisk component of the first stage of the high-pressure compressor is likely to receive foreign bodies such as ice cubes, birds or others.
  • the rotor part of the compressor is driven in rotation by a shaft S driven itself in rotation by a turbine located in downstream of the compressor. The axis of rotation is noted B.
  • the denomination "upstream” or “downstream” of the rotor elements is to be interpreted according to the SF direction of the air flow in the compressor.
  • the "internal” denomination respectively "outer” rings (or part of a ring) terminating a piece is to be interpreted as rings extending inward from the room, namely rings leaving the room and whose radius decreases, respectively rings extending towards the outside of the room, namely rings leaving the room and whose radius increases.
  • FIG. 2 shows the connection between the bladed disks D1 and D2 according to the invention.
  • the rotor line is advantageously continuous at the inlet of the high-pressure compressor.
  • the rotor comprises, at the compressor inlet, a flange-shaped journal 30 terminated by a radial ring 32.
  • the disk D2 comprises an upstream flange 20 extending towards the trunnion and ending in a radial ring 22 whose upstream surface comes into contact with the downstream surface of the radial ring 32 of the pin.
  • the blisk D1 monobloc includes a downstream flange 10 extending towards the radial ring 32 of the trunnion and ending by a radial ring 12 whose downstream surface comes into contact with the upstream surface of the radial ring 32.
  • the blisk D1, the pin 30 and the disk D2 are connected between them by a fastening means such as a screw-nut system 40 shown in FIG. 2 passing through holes facing rings 12, 32 and 22.
  • the downstream flange 10 to symmetry of revolution of the monobloc blisk D1 makes it possible to carry out a link downstream of this disk with the rotor to meet the criteria of vibration resistance, service life, and withstand the loss of blades of this disk of the first compression stage.
  • radial ring is meant a ring located in a radial plane, namely a plane perpendicular to the axis of rotation of the rotor.
  • the rings could be inclined relative to the radial plane provided that their inclination allows the relative placement of the surfaces of the rings against each other as described above.
  • FIG. 3 represents the one-piece disk D1 without blade, this disk being able to receive blades.
  • This first piece of the rotor comprises a circular foot 11 surmounted by a plate circular 18 adapted to receive blades.
  • the circular foot 11 comprises the downstream flange circular 10 extending as an example in the direction of the axis of rotation B and is ending with the radial ring 12 provided with a succession of holes 14 and notches 16.
  • the radial ring 12 comprises thirty two holes and eight notches distributed symmetrically between the thirty-two holes.
  • the ring radial 12 is an outer ring.
  • FIG. 4 represents a second part of the rotor, namely the journal 30 comprising a first cylindrical upstream portion 31 flaring in a frustoconical portion 33, the latter terminating downstream by a radial ring 32.
  • This radial ring is composed of a part internal radial 35 called foot and an outer radial portion terminated by a flange 38 extending axially upstream and downstream.
  • the outer radial portion includes holes 34 intended to be put face to face with the holes and the notches of the radial ring 12 of the upstream disk D1 on the side of the upstream surface of the radial ring 32 and with the holes in the radial ring 22 of the downstream disk D2 on the downstream surface side of the radial ring 32.
  • FIG. 5 represents the disk D2 without blade, this disk being able to receive blades.
  • This second piece of the rotor comprises a circular foot 21 surmounted by a plate circular 28 adapted to receive blades.
  • the circular foot 21 comprises the downstream flange circular 20 narrowing upstream in frustoconical form and ending in the ring radial 22 provided with a succession of holes 24.
  • the radial ring 22 is internal and includes forty holes. Notches 26 are distributed between the holes 24 in order to reduce the amount of material of the radial ring 22. These notches serve also as a means of indicating the position of the holes 24.
  • Figures 6 and 7 show the steps of mounting a connection according to the invention.
  • the journal is connected to the disk D2 by positioning the downstream surface of the outer radial ring 32 against the upstream surface of the radial ring internal 22 of the downstream disk D2 while putting in face the holes of the external radial ring 32 and the holes of the inner radial ring 22.
  • First fixing means such as screw / nut systems, are put in place in some of the holes opposite, these holes being detectable from the notches 26 of the inner radial ring 22 for example. So, these marked holes correspond to the center holes of the set of holes located between two notches 26 as an example.
  • the holes identified must correspond to the distribution of notches 16 of the disk D1 for the reasons developed later.
  • the rotor line is continuous even in the absence of D1 upstream disk, in other words, the stream of air flow is maintained.
  • the trunnion 30 and the disk D2 form an assembly fixed by the first fixing means, this assembly is called the second / third rotor assembly.
  • the remaining holes are equipped a part of second fixing means, for example of screw without nut, the head of the screw being pressed against the downstream surface of the internal radial ring 22 of the disk D2 and the end the stem of the screw protruding largely from the side of the upstream surface of the radial ring 32 of the journal 30 so as to receive the thickness of the outer radial ring 12 of the disc D1 then the fixing nut.
  • the screws of the second securing means are retained by a ring thus avoiding the screws out holes when the nuts are not yet engaged on the screw rods.
  • Nuts are screwed onto the ends of the screws and are tight against the upstream surface of the outer radial ring 12 of the disk D1.
  • the axial rim 38 of the ring external radial 32 of the trunnion covers upstream the radial outer edge of the radial ring 12 of the disk D1, and downstream the radial outer edge of the inner radial ring 22 of the D2 disk.
  • the axial flange 38 thus makes it possible to exert a centripetal radial force on the outer radial ring 12 of the disk D1 and on the internal radial ring 22 of the disk D2, especially in operation.
  • Disassembly of the connection between the disk D1 and the trunnion / disk assembly D2 is carried out as following.
  • the stator is partly removed to be able to have access to the fastening means located behind the disk D1.
  • the nuts of the second fastening means are unscrewed and removed.
  • the disk D1 can then be withdrawn by axial traction upstream. It remains the pin and the disk D2 fixed together by the first fixing means, for example by eight screw-nut systems, and it remains the ends of the screw rods of the second fastening means retained by the rushes.
  • the monoblock disk D1 can be removed from the rotor with great ease and without have to break the rotor line.
  • the monobloc disc D1 can be repaired or replaced by another monoblock disk D1 in good condition.
  • the editing of this disk D1 is done as stated above by matching the notches 16 with the first means of fixation and the holes 14 with a part of the second fixing means, namely the rods of screw.
  • connection of the connection according to the embodiment of FIGS. 6 and 7 is carried out without the presence of the stator which is arranged after establishment of the connection.
  • a variant of this mode implementation would allow a connection of the connection with the presence of the stator: the systems The screws / nuts must then be reversed (the nut is located in place of the screw head and Conversely).
  • FIG. 8 represents an alternative embodiment of the connection according to the invention.
  • the disk DD1 consists of a flange 110 extending axially so slightly inclined and ending with an internal radial ring 112 adapted to be placed against the upstream surface of the outer radial ring 132 of the pin 130.
  • the ring 112 comprises a succession of holes and notches like ring 12.
  • the DD2 disk is the same as the disk D2 and its internal radial ring 122 is able to be placed against the downstream surface of the outer radial ring 132 of the pin 130.
  • the rings 132 and 122 are made as the rings 32 and 22.
  • the disk DD 1 comprises a shortened foot compared to the embodiment previous disk D1 so that it is possible to access the fastening means 140, similar to the fixing means 40 of the previous embodiment, by a passage between the foot of the DD1 disk and the trunnion 130.
  • This embodiment makes it possible in particular not to have to remove the stator during assembly or disassembly of the DD1 disk. Otherwise, the assembly and disassembly procedure corresponds to those previously described.
  • the first fastening means of the trunnion / disc D2 assembly are shorter than the second fixing means for fixing the first ring circular to the trunnion / disc D2 assembly.
  • the invention thus makes it possible to replace without particular maintenance or loss of time, the bladed monoblock disc, the most problematic part in service and having the most impact on compressor performance.
  • the invention is not limited to a bolted connection between a disk, the first rotor part and a fixed set of second and third rotor pieces but can extend to any piece requiring separate disassembly with a set of parts fixed together.

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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 disk has a clamp connected to a circular ring placed against a trunnion (30) fixed to a blade disk (D2) by fixation holes. The ring has recesses to bypass the fixation holes of the trunnion or disk (D2), and holes placed opposite to the fixation holes of the trunnion or disk for fixing the ring to trunnion or disk. The trunnion and the disk (D2) have a symmetry of revolution of the rotor. Independent claims are also included for the following: (a) a method for mounting connection between blade disks of a compressor rotor (b) a method for dismounting the connection between blade disks of a compressor rotor.

Description

L'invention concerne le domaine des compresseurs haute-pression de turboréacteur, et plus particulièrement celui de la liaison entre le disque aubagé du premier étage du rotor du compresseur et le disque aubagé du deuxième étage du rotor du compresseur.The invention relates to the field of high-pressure turbojet compressors, and more particularly that of the connection between the bladed disk of the first stage of the rotor of the compressor and the bladed disc of the second stage of the compressor rotor.

Dans le cas de turboréacteurs d'avion, le compresseur reçoit le flux d'air d'entrée. Le disque aubagé à l'entrée du compresseur est susceptible de recevoir des corps étrangers tels que glaçons, oiseaux ou autres. Parmi les différents disques aubagés du compresseur, le premier est ainsi le plus exposé aux endommagements par des corps étrangers. De ce fait, il est également celui qui requiert des opérations de maintenance pouvant nécessiter le démontage du disque aubagé. Tout démontage de la ligne rotor du compresseur comprenant différentes pièces entraíne des opérations d'équilibrage et d'alignement qui nécessite un passage en atelier de maintenance qualifié et outillé. Lors de ces opérations de démontage, il est important que la ligne rotor ne soit pas rompue.In the case of aircraft turbojets, the compressor receives the inlet air flow. The disc bladed at the compressor inlet is likely to receive foreign bodies such as ice cubes, birds or others. Among the different blower discs of the compressor, the first is thus most exposed to damage by foreign bodies. Because of this, it is also the one that requires maintenance operations that may require disassembly of the blisk. Any disassembly of the rotor line of the compressor including different parts leads to balancing and alignment operations that require a transition to qualified and equipped maintenance workshop. During these dismantling operations, it is important that the rotor line is not broken.

Une solution a été proposée dans EP 1122 443 où un disque aubagé monobloc (DAM) est utilisé comme premier disque aubagé du compresseur. Ce disque aubagé est fixé par une bride amont à l'entrée du compresseur. Toutefois, cette solution n'apporte pas entière satisfaction puisqu'elle ne permet pas de respecter certains critères relatifs au disque aubagé par exemple un critère de tenue aux vibrations, un critère de durée de vie, ou un critère de tenue à la perte d'aubes.A solution has been proposed in EP 1122 443 where a monobloc blisk (DAM) is used as the first blisk of the compressor. This blisk is fixed by a upstream flange at the compressor inlet. However, this solution does not bring complete satisfaction because it does not allow to meet certain criteria relating to the blisk. for example a vibration resistance criterion, a lifetime criterion, or a criterion of held at the loss of blades.

La présente invention vient améliorer la situation.The present invention improves the situation.

L'invention concerne une pièce pour rattachement à l'entrée d'un rotor de compresseur, cette pièce étant apte à constituer une première pièce d'un rotor de compresseur.The invention relates to a part for attachment to the inlet of a compressor rotor, this piece being able to constitute a first part of a compressor rotor.

Selon une caractéristique essentielle de l'invention, la pièce est terminée par un premier anneau muni d'une succession de trous et d'encoches.According to an essential characteristic of the invention, the piece is terminated by a first ring with a succession of holes and notches.

Selon une autre caractéristique de l'invention, l'axe du premier anneau est apte à être centré sur l'axe de rotation du rotor de compresseur pour rattachement à l'entrée du rotor de compresseur, le premier anneau est apte à être placé contre une deuxième pièce à symétrie de révolution du rotor fixée à une troisième pièce à symétrie de révolution du rotor par des moyens de fixation et formant un ensemble deuxième/troisième pièces du rotor, les encoches étant aptes à contourner les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor, les trous du premier anneau étant aptes à être placés en vis à vis de trous de l'ensemble deuxième/troisième pièces pour fixation du premier anneau à l'ensemble deuxième/troisième pièces.According to another characteristic of the invention, the axis of the first ring is adapted to be centered on the axis of rotation of the compressor rotor for attachment to the rotor inlet of compressor, the first ring is able to be placed against a second symmetry piece rotor revolution fixed to a third rotor symmetry piece by fastening means and forming a set second / third rotor parts, the notches being able to bypass the fastening means of the set second / third parts of the rotor, the holes of the first ring being able to be placed opposite the holes of the assembly second / third pieces for fixing the first ring to the second / third set rooms.

Préférentiellement, le premier anneau est dans un plan perpendiculaire à l'axe de rotation du rotor.Preferably, the first ring is in a plane perpendicular to the axis of rotation of the rotor.

Avantageusement, la pièce comprend un disque et des aubes attachées sur sa périphérie.Advantageously, the part comprises a disc and blades attached on its periphery.

En outre, la pièce comprend un disque muni d'une bride reliée au premier anneau, la bride et l'anneau étant placés en aval du disque de façon que la fixation du disque avec l'ensemble deuxième/troisième pièces puisse s'effectuer en aval du disque par rapport au sens d'écoulement du flux dans le compresseur.In addition, the part comprises a disk provided with a flange connected to the first ring, the flange and the ring being placed downstream of the disc so that the attachment of the disc with the assembly second / third parts can be performed downstream of the disc relative to the direction Flow flow in the compressor.

L'invention concerne également une liaison entre une première pièce comme définie précédemment, terminée par un premier anneau muni d'une succession de trous et d'encoches, l'axe du premier anneau étant centré sur l'axe de rotation du rotor de compresseur pour rattachement à l'entrée du rotor de compresseur, et un ensemble d'une deuxième pièce de rotor fixée à une troisième pièce de rotor, la deuxième pièce formant l'entrée du rotor de compresseur et étant terminée en aval par un deuxième anneau comprenant des trous, la troisième pièce étant terminée en amont par un troisième anneau comprenant des trous, les deuxième et troisième anneaux étant disposés l'un contre l'autre, de manière à placer leurs trous en vis à vis, et étant fixés entre eux par des premiers moyens de fixation, le premier anneau circulaire étant disposé en amont de et contre l'ensemble deuxième/troisième pièces de façon à ce que les encoches contournent les premiers moyens de fixation de l'ensemble deuxième/troisième pièces du rotor et à ce que au moins certains des trous du premier anneau soient en vis à vis de trous de l'ensemble deuxième/troisième pièces, des seconds moyens de fixation fixant le premier anneau circulaire à l'ensemble deuxième/troisième pièces.The invention also relates to a connection between a first piece as defined previously, terminated by a first ring provided with a succession of holes and of notches, the axis of the first ring being centered on the axis of rotation of the rotor of compressor for attachment to the compressor rotor inlet, and a set of a second rotor piece attached to a third rotor piece, the second piece forming the input of the compressor rotor and being terminated downstream by a second ring comprising holes, the third piece being terminated upstream by a third ring comprising holes, the second and third rings being arranged one against the other, so as to place their holes facing each other, and being fixed between them by first means fixing, the first circular ring being disposed upstream of and against the assembly second / third pieces so that the notches circumvent the first means securing the second / third rotor assembly and that at least some holes of the first ring are opposite holes of the set second / third parts, second fixing means fixing the first circular ring to the assembly second / third pieces.

Préférentiellement, les deuxième et troisième anneaux sont dans un plan perpendiculaire à l'axe de rotation du rotor.Preferably, the second and third rings are in a plane perpendicular to the axis of rotation of the rotor.

Avantageusement, les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor sont plus courts que les moyens de fixation permettant de fixer le premier anneau à l'ensemble deuxième/troisième pièces.Advantageously, the fastening means of the assembly of second / third rotor parts are shorter than the fixing means for fixing the first ring to the whole second / third pieces.

En outre, les moyens de fixation comprennent des systèmes vis-écrou. In addition, the fastening means comprise screw-nut systems.

Préférentiellement, la vis du système vis-écrou est retenue par un jonc permettant à la vis de tenir en cas d'absence de l'écrou.Preferably, the screw of the screw-nut system is retained by a ring allowing the screw to hold in case of absence of the nut.

L'invention concerne notamment une turbomachine comprenant un compresseur haute-pression muni d'une liaison comme décrite plus haut.The invention relates in particular to a turbomachine comprising a high-pressure compressor provided with a link as described above.

L'invention concerne de plus un procédé de montage d'une liaison comme décrite précédemment, consistant à placer les deuxième et troisième anneaux circulaires l'un contre l'autre, de manière à placer leurs trous en vis à vis, à fixer ces deuxième et troisième anneaux entre eux par des premiers moyens de fixation traversant certains des trous, à placer dans les trous restant des seconds moyens de fixation aptes à fixer l'ensemble deuxième/troisième pièce à la première pièce, à placer le premier anneau circulaire en amont de et contre l'ensemble deuxième/troisième pièce de façon à ce que les encoches contournent les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor et à ce que certains des trous du premier anneau soient traversés par les seconds moyens de fixation afin de fixer le premier anneau circulaire à l'ensemble deuxième/troisième pièces.The invention further relates to a method of mounting a link as described previously, of placing the second and third circular rings one against the other, so as to place their holes opposite, to fix these second and third rings between them by first fixing means passing through some of the holes, to be placed in the remaining holes of the second fixing means capable of fixing the second / third assembly piece to the first piece, to place the first circular ring upstream of and against the whole second / third piece so that the notches circumvent the means fixing the entire second / third rotor parts and that some of the holes the first ring are traversed by the second fastening means in order to fix the first circular ring to the second / third pieces set.

L'invention concerne en outre un procédé de démontage d'une liaison comme décrite précédemment, consistant à défaire les seconds moyens de fixation pour enlever la première pièce du rotor de compresseur et conserver l'ensemble deuxième pièce/troisième pièce du rotor.The invention further relates to a method of disassembling a link as described previously, of undoing the second fastening means to remove the first compressor rotor part and keep the whole second piece / third piece of the rotor.

Les figures ci-après illustrent de manière non limitative des modes de réalisation de l'invention :

  • la figure 1 représente une demi-vue en coupe selon l'axe de rotation d'un compresseur de turboréacteur composé de différents disques aubagés,
  • la figure 2 représente en détail les premier et deuxième disques aubagés de compresseur de la figure 1 reliés entre-eux par une liaison selon l'invention,
  • la figure 3 représente un secteur en relief du premier disque sans aube selon l'invention,
  • la figure 4 représente un secteur en relief du tourillon selon l'invention,
  • la figure 5 représente un secteur en relief du deuxième disque sans aube selon l'invention,
  • la figure 6 représente la première phase du montage de la liaison selon l'invention consistant en l'assemblage du tourillon et du deuxième disque,
  • la figure 7 représente la deuxième phase du montage de la liaison selon l'invention consistant en l'assemblage du premier disque avec l'ensemble du tourillon et du deuxième disque,
  • la figure 8 représente une variante de réalisation de la liaison selon l'invention.
The following figures illustrate in a nonlimiting manner embodiments of the invention:
  • FIG. 1 represents a half-view in section along the axis of rotation of a turbojet compressor composed of various bladed disks,
  • FIG. 2 shows in detail the first and second compressor bladed discs of FIG. 1 interconnected by a link according to the invention,
  • FIG. 3 represents a sector in relief of the first disk without blade according to the invention,
  • FIG. 4 represents a sector in relief of the journal according to the invention,
  • FIG. 5 represents a sector in relief of the second disk without blade according to the invention,
  • FIG. 6 represents the first phase of the assembly of the connection according to the invention consisting of the assembly of the journal and the second disc,
  • FIG. 7 represents the second phase of the assembly of the connection according to the invention consisting of the assembly of the first disc with the whole of the journal and the second disc,
  • FIG. 8 represents an alternative embodiment of the connection according to the invention.

Les dessins contiennent, pour l'essentiel, des éléments de caractère certain. Ils pourront donc non seulement servir à mieux faire comprendre la description, mais aussi contribuer à la définition de l'invention, le cas échéant.The drawings contain, for the most part, elements of a certain character. They will be able not only to make the description better understood, but also to contribute to the definition of the invention, if any.

La figure 1 représente une coupe partielle de la partie rotor d'un compresseur haute-pression de turboréacteur composé de différents étages de compression E1 à E5, comprenant chacun un disque D1 à D5 muni d'une couronne d'aubes A1 à A5. Chaque étage de compression est également composé, en aval de chaque disque aubagé, d'un redresseur de flux non représenté et faisant partie de la partie stator du compresseur. Chaque redresseur permet de redresser le flux d'air avant l'entrée dans le prochain étage de compression. La partie rotor et la partie stator du compresseur délimitent une "veine" pour le flux d'air à comprimer. On parle de ligne rotor pour désigner la surface extérieure continue du rotor formant la limite inférieur de cette veine. Les disques aubagés D2 à D5 du compresseur sont formés en une seule pièce appelée ensemble de disques. Le disque aubagé D1 est avantageusement un disque aubagé monobloc rattaché au rotor en amont de l'ensemble de disques pour pouvoir être facilement démonté aux fins de maintenance et d'entretien. Ce premier disque aubagé monobloc composant le premier étage du compresseur haute-pression est susceptible de recevoir des corps étrangers tels que glaçons, oiseaux ou autres. La partie rotor du compresseur est entraínée en rotation par un arbre S entraíné lui-même en rotation par une turbine située en aval du compresseur. L'axe de rotation est noté B.FIG. 1 represents a partial section of the rotor part of a high-pressure compressor turbojet engine composed of different stages of compression E1 to E5, each comprising a disk D1 to D5 provided with a blade ring A1 to A5. Each compression stage is also composed, downstream of each blisk, of a not shown flow rectifier and forming part of the stator part of the compressor. Each rectifier straighten the airflow before entering the next compression stage. The rotor part and the part compressor stator delimit a "vein" for the airflow to be compressed. We are talking about rotor line to denote the continuous outer surface of the rotor forming the lower limit of this vein. The bladed discs D2 to D5 of the compressor are formed in one piece called set of disks. The bladed disk D1 is advantageously a blisk. monobloc attached to the rotor upstream of the set of discs to be easily disassembled for maintenance and servicing. This first blisk component of the first stage of the high-pressure compressor is likely to receive foreign bodies such as ice cubes, birds or others. The rotor part of the compressor is driven in rotation by a shaft S driven itself in rotation by a turbine located in downstream of the compressor. The axis of rotation is noted B.

La dénomination "amont" ou "aval" des éléments du rotor est à interpréter en fonction du sens SF du flux d'air dans le compresseur. La dénomination "interne" respectivement "externe" des anneaux (ou partie d'anneau) terminant une pièce est à interpréter comme des anneaux s'étendant vers l'intérieur de la pièce, à savoir des anneaux partant de la pièce et dont le rayon diminue, respectivement des anneaux s'étendant vers l'extérieur de la pièce, à savoir des anneaux partant de la pièce et dont le rayon augmente.The denomination "upstream" or "downstream" of the rotor elements is to be interpreted according to the SF direction of the air flow in the compressor. The "internal" denomination respectively "outer" rings (or part of a ring) terminating a piece is to be interpreted as rings extending inward from the room, namely rings leaving the room and whose radius decreases, respectively rings extending towards the outside of the room, namely rings leaving the room and whose radius increases.

La figure 2 représente la liaison entre les disques aubagés D1 et D2 selon l'invention. La ligne du rotor est avantageusement continue à l'entrée du compresseur haute-pression. Le rotor comprend, à l'entrée du compresseur, un tourillon 30 de forme évasée terminé par un anneau radial 32. Le disque D2 comprend une bride amont 20 s'étendant en direction du tourillon et se terminant par un anneau radial 22 dont la surface amont vient en contact avec la surface aval de l'anneau radial 32 du tourillon. Le disque aubagé monobloc D1 comprend une bride aval 10 s'étendant en direction de l'anneau radial 32 du tourillon et se terminant par un anneau radial 12 dont la surface aval vient en contact avec la surface amont de l'anneau radial 32. Le disque aubagé monobloc D1, le tourillon 30 et le disque D2 sont reliés entre-eux par un moyen de fixation comme un système vis-écrou 40 représenté sur la figure 2 passant à travers des trous en vis à vis des anneaux 12, 32 et 22. La bride aval 10 à symétrie de révolution du disque aubagé monobloc D1 permet de réaliser une liaison aval de ce disque avec le rotor pour répondre aux critères de tenue aux vibrations, de durée de vie, et de tenue à la perte d'aubes de ce disque du premier étage de compression.FIG. 2 shows the connection between the bladed disks D1 and D2 according to the invention. The rotor line is advantageously continuous at the inlet of the high-pressure compressor. The rotor comprises, at the compressor inlet, a flange-shaped journal 30 terminated by a radial ring 32. The disk D2 comprises an upstream flange 20 extending towards the trunnion and ending in a radial ring 22 whose upstream surface comes into contact with the downstream surface of the radial ring 32 of the pin. The blisk D1 monobloc includes a downstream flange 10 extending towards the radial ring 32 of the trunnion and ending by a radial ring 12 whose downstream surface comes into contact with the upstream surface of the radial ring 32. The blisk D1, the pin 30 and the disk D2 are connected between them by a fastening means such as a screw-nut system 40 shown in FIG. 2 passing through holes facing rings 12, 32 and 22. The downstream flange 10 to symmetry of revolution of the monobloc blisk D1 makes it possible to carry out a link downstream of this disk with the rotor to meet the criteria of vibration resistance, service life, and withstand the loss of blades of this disk of the first compression stage.

Par anneau radial, on entend un anneau situé dans un plan radial, à savoir un plan perpendiculaire à l'axe de rotation du rotor. Toutefois, les anneaux pourraient être inclinés par rapport au plan radial à condition que leur inclinaison permettent le placement relatif des surfaces des anneaux les unes contre les autres comme décrit plus haut.By radial ring is meant a ring located in a radial plane, namely a plane perpendicular to the axis of rotation of the rotor. However, the rings could be inclined relative to the radial plane provided that their inclination allows the relative placement of the surfaces of the rings against each other as described above.

Chaque élément ou pièce de la liaison est plus particulièrement détaillé en référence aux figures 3, 4 et 5.Each element or part of the link is more particularly detailed with reference to Figures 3, 4 and 5.

La figure 3 représente le disque monobloc D1 sans aube, ce disque étant apte à recevoir des aubes. Cette première pièce du rotor comprend un pied circulaire 11 surmonté d'un plateau circulaire 18 apte à recevoir des aubes. Le pied circulaire 11 comprend la bride aval circulaire 10 s'étendant à titre d'exemple dans la direction de l'axe de rotation B et se terminant par l'anneau radial 12 muni d'une succession de trous 14 et d'encoches 16. Dans un exemple de réalisation, l'anneau radial 12 comprend trente deux trous et huit encoches répartis symétriquement entre les trente deux trous. Dans la réalisation de la figure, l'anneau radial 12 est un anneau externe.FIG. 3 represents the one-piece disk D1 without blade, this disk being able to receive blades. This first piece of the rotor comprises a circular foot 11 surmounted by a plate circular 18 adapted to receive blades. The circular foot 11 comprises the downstream flange circular 10 extending as an example in the direction of the axis of rotation B and is ending with the radial ring 12 provided with a succession of holes 14 and notches 16. In an exemplary embodiment, the radial ring 12 comprises thirty two holes and eight notches distributed symmetrically between the thirty-two holes. In the embodiment of the figure, the ring radial 12 is an outer ring.

La figure 4 représente une deuxième pièce du rotor, à savoir le tourillon 30 comprenant une première partie amont cylindrique 31 s'évasant en une partie tronconique 33, cette dernière se terminant en aval par un anneau radial 32. Cet anneau radial est composé d'une partie radiale interne 35 appelée pied et d'une partie radiale externe terminée par un rebord 38 s'étendant axialement vers l'amont et vers l'aval. La partie radiale externe comprend des trous 34 destinés à être mis en vis à vis avec les trous et les encoches de l'anneau radial externe 12 du disque amont D1 du côté de la surface amont de l'anneau radial 32 et avec les trous de l'anneau radial 22 du disque aval D2 du côté de la surface aval de l'anneau radial 32.FIG. 4 represents a second part of the rotor, namely the journal 30 comprising a first cylindrical upstream portion 31 flaring in a frustoconical portion 33, the latter terminating downstream by a radial ring 32. This radial ring is composed of a part internal radial 35 called foot and an outer radial portion terminated by a flange 38 extending axially upstream and downstream. The outer radial portion includes holes 34 intended to be put face to face with the holes and the notches of the radial ring 12 of the upstream disk D1 on the side of the upstream surface of the radial ring 32 and with the holes in the radial ring 22 of the downstream disk D2 on the downstream surface side of the radial ring 32.

La figure 5 représente le disque D2 sans aube, ce disque étant apte à recevoir des aubes. Cette deuxième pièce du rotor comprend un pied circulaire 21 surmonté d'un plateau circulaire 28 apte à recevoir des aubes. Le pied circulaire 21 comprend la bride aval circulaire 20 se resserrant vers l'amont sous forme tronconique et se terminant par l'anneau radial 22 muni d'une succession de trous 24. Dans un exemple de réalisation, l'anneau radial 22 est interne et comprend quarante trous. Des encoches 26 sont réparties entre les trous 24 de manière à diminuer la quantité de matière de l'anneau radial 22. Ces encoches servent également comme moyen d'indication de la position des trous 24.FIG. 5 represents the disk D2 without blade, this disk being able to receive blades. This second piece of the rotor comprises a circular foot 21 surmounted by a plate circular 28 adapted to receive blades. The circular foot 21 comprises the downstream flange circular 20 narrowing upstream in frustoconical form and ending in the ring radial 22 provided with a succession of holes 24. In an exemplary embodiment, the radial ring 22 is internal and includes forty holes. Notches 26 are distributed between the holes 24 in order to reduce the amount of material of the radial ring 22. These notches serve also as a means of indicating the position of the holes 24.

Les figures 6 et 7 représentent les étapes de montage d'une liaison selon l'invention.Figures 6 and 7 show the steps of mounting a connection according to the invention.

Selon la figure 6, dans une première étape, le tourillon est relié au disque D2 en positionnant la surface aval de l'anneau radial externe 32 contre la surface amont de l'anneau radial interne 22 du disque aval D2 tout en mettant en vis à vis les trous de l'anneau radial externe 32 et les trous de l'anneau radial interne 22. Des premiers moyens de fixation, comme des systèmes vis/écrou, sont mis en place dans certains des trous en vis à vis, ces trous étant repérables à partir des encoches 26 de l'anneau radial interne 22 par exemple. Ainsi, ces trous repérés correspondent aux trous centraux de l'ensemble de trous situés entre deux encoches 26 à titre d'exemple. Les trous repérés doivent correspondre à la répartition des encoches 16 du disque D1 pour les raisons développées plus loin. Grâce à la présence de la liaison entre le tourillon et le disque D2, la ligne rotor est continue même en absence de disque amont D1, en d'autres termes, la veine du flux d'air est maintenue. Le tourillon 30 et le disque D2 forment un ensemble fixé par les premiers moyens de fixation, cet ensemble est appelé l'ensemble deuxième/troisième pièces du rotor. Les trous restants sont munis d'une partie de seconds moyens de fixation, par exemple de vis sans écrou, la tête de la vis étant appuyée contre la surface aval de l'anneau radial interne 22 du disque D2 et l'extrémité de la tige de la vis dépassant largement du côté de la surface amont de l'anneau radial externe 32 du tourillon 30 de façon à pouvoir recevoir l'épaisseur de l'anneau radial externe 12 du disque D1 puis l'écrou de fixation. De manière avantageuse, les vis des seconds moyens de fixation sont retenues par un jonc évitant ainsi aux vis de sortir des trous lorsque les écrous ne sont pas encore engagés sur les tiges de vis.According to FIG. 6, in a first step, the journal is connected to the disk D2 by positioning the downstream surface of the outer radial ring 32 against the upstream surface of the radial ring internal 22 of the downstream disk D2 while putting in face the holes of the external radial ring 32 and the holes of the inner radial ring 22. First fixing means, such as screw / nut systems, are put in place in some of the holes opposite, these holes being detectable from the notches 26 of the inner radial ring 22 for example. So, these marked holes correspond to the center holes of the set of holes located between two notches 26 as an example. The holes identified must correspond to the distribution of notches 16 of the disk D1 for the reasons developed later. Thanks to the presence of the connection between the journal and the disk D2, the rotor line is continuous even in the absence of D1 upstream disk, in other words, the stream of air flow is maintained. The trunnion 30 and the disk D2 form an assembly fixed by the first fixing means, this assembly is called the second / third rotor assembly. The remaining holes are equipped a part of second fixing means, for example of screw without nut, the head of the screw being pressed against the downstream surface of the internal radial ring 22 of the disk D2 and the end the stem of the screw protruding largely from the side of the upstream surface of the radial ring 32 of the journal 30 so as to receive the thickness of the outer radial ring 12 of the disc D1 then the fixing nut. Advantageously, the screws of the second securing means are retained by a ring thus avoiding the screws out holes when the nuts are not yet engaged on the screw rods.

Selon la figure 7, dans une deuxième étape, l'axe du disque D1 est centré sur l'axe de rotation du rotor de compresseur pour le rattachement à l'entrée du rotor du compresseur. Ainsi, l'anneau radial externe 12 est placé contre la surface amont de l'anneau radial externe 32 du tourillon. Pour ce faire:

  • les encoches 16 sont d'abord placées en vis à vis des premiers moyens de fixation puis contournent ces derniers une fois l'anneau radial externe 12 placé contre la surface amont de l'anneau radial externe 32,
  • les trous 14 du premier anneau 12 sont placés en vis à vis des trous restants de l'ensemble deuxième/troisième pièces du rotor, en d'autres termes, les trous 14 sont pénétrés par les extrémités des tiges de vis des seconds moyens de fixation qui dépassent de la surface amont de l'anneau radial externe 12 du disque D1.
According to FIG. 7, in a second step, the axis of the disk D1 is centered on the axis of rotation of the compressor rotor for attachment to the inlet of the rotor of the compressor. Thus, the outer radial ring 12 is placed against the upstream surface of the outer radial ring 32 of the pin. To do this:
  • the notches 16 are first placed opposite the first fastening means and then bypass the latter once the outer radial ring 12 placed against the upstream surface of the outer radial ring 32,
  • the holes 14 of the first ring 12 are placed opposite the remaining holes of the second / third rotor assembly, in other words, the holes 14 are penetrated by the ends of the screw rods of the second fastening means protruding from the upstream surface of the outer radial ring 12 of the disk D1.

Des écrous sont vissés sur les extrémités des vis et sont serrés contre la surface amont de l'anneau radial externe 12 du disque D1. Avantageusement, le rebord 38 axial de l'anneau radial externe 32 du tourillon recouvre en amont le bord externe radial de l'anneau radial externe 12 du disque D1, et en aval le bord externe radial de l'anneau radial interne 22 du disque D2. Le rebord axial 38 permet ainsi d'exercer une force radiale centripète sur l'anneau radial externe 12 du disque D1 et sur l'anneau radial interne 22 du disque D2, notamment en fonctionnement.Nuts are screwed onto the ends of the screws and are tight against the upstream surface of the outer radial ring 12 of the disk D1. Advantageously, the axial rim 38 of the ring external radial 32 of the trunnion covers upstream the radial outer edge of the radial ring 12 of the disk D1, and downstream the radial outer edge of the inner radial ring 22 of the D2 disk. The axial flange 38 thus makes it possible to exert a centripetal radial force on the outer radial ring 12 of the disk D1 and on the internal radial ring 22 of the disk D2, especially in operation.

Le démontage de la liaison entre le disque D1 et l'ensemble tourillon/disque D2 s'effectue comme suit. Dans la réalisation de la figure 2, le stator est en partie enlevé pour pouvoir avoir accès aux moyens de fixation situés en arrière du disque D1.Disassembly of the connection between the disk D1 and the trunnion / disk assembly D2 is carried out as following. In the embodiment of Figure 2, the stator is partly removed to be able to have access to the fastening means located behind the disk D1.

Les écrous des seconds moyens de fixation sont dévissés et enlevés. Le disque D1 peut alors être retiré par traction axiale vers l'amont. Il reste le tourillon et le disque D2 fixés ensemble par les premiers moyens de fixation, par exemple par huit systèmes vis-écrou, et il reste également les extrémités des tiges de vis des seconds moyens de fixation retenus par les joncs. Ainsi, le disque monobloc D1 peut être enlevé du rotor avec une grande facilité et sans avoir à rompre la ligne du rotor. Le disque monobloc D1 peut être réparé ou remplacé par un autre disque monobloc D1 en bon état. Le montage de ce disque D1 s'effectue comme énoncé plus haut en faisant correspondre les encoches 16 avec les premiers moyens de fixation et les trous 14 avec une partie des seconds moyens de fixation, à savoir les tiges de vis.The nuts of the second fastening means are unscrewed and removed. The disk D1 can then be withdrawn by axial traction upstream. It remains the pin and the disk D2 fixed together by the first fixing means, for example by eight screw-nut systems, and it remains the ends of the screw rods of the second fastening means retained by the rushes. Thus, the monoblock disk D1 can be removed from the rotor with great ease and without have to break the rotor line. The monobloc disc D1 can be repaired or replaced by another monoblock disk D1 in good condition. The editing of this disk D1 is done as stated above by matching the notches 16 with the first means of fixation and the holes 14 with a part of the second fixing means, namely the rods of screw.

Le montage de la liaison selon le mode de réalisation des figures 6 et 7 s'effectue sans la présence du stator qui est disposé après mise en place de la liaison. Une variante de ce mode de réalisation permettrait un montage de la liaison avec la présence du stator : les systèmes vis/écrous doivent alors être inversés (l'écrou étant situé à la place de la tête de la vis et inversement).The connection of the connection according to the embodiment of FIGS. 6 and 7 is carried out without the presence of the stator which is arranged after establishment of the connection. A variant of this mode implementation would allow a connection of the connection with the presence of the stator: the systems The screws / nuts must then be reversed (the nut is located in place of the screw head and Conversely).

La figure 8 représente une variante de réalisation de la liaison selon l'invention.FIG. 8 represents an alternative embodiment of the connection according to the invention.

Ainsi, le disque DD1 est constitué d'une bride 110 s'étendant axialement de façon légèrement inclinée et se terminant par un anneau radial interne 112 apte à être placé contre la surface amont de l'anneau radial externe 132 du tourillon 130. L'anneau 112 comprend une succession de trous et d'encoches comme l'anneau 12. Le disque DD2 est le même que le disque D2 et son anneau radial interne 122 est apte à être placé contre la surface aval de l'anneau radial externe 132 du tourillon 130. Les anneaux 132 et 122 sont réalisés comme les anneaux 32 et 22. Le disque DD 1 comprend un pied raccourci par rapport à la réalisation précédente du disque D1 de sorte qu'il est possible d'accéder aux moyens de fixation 140, semblables aux moyens de fixation 40 de la réalisation précédente, par un passage entre le pied du disque DD1 et le tourillon 130.Thus, the disk DD1 consists of a flange 110 extending axially so slightly inclined and ending with an internal radial ring 112 adapted to be placed against the upstream surface of the outer radial ring 132 of the pin 130. The ring 112 comprises a succession of holes and notches like ring 12. The DD2 disk is the same as the disk D2 and its internal radial ring 122 is able to be placed against the downstream surface of the outer radial ring 132 of the pin 130. The rings 132 and 122 are made as the rings 32 and 22. The disk DD 1 comprises a shortened foot compared to the embodiment previous disk D1 so that it is possible to access the fastening means 140, similar to the fixing means 40 of the previous embodiment, by a passage between the foot of the DD1 disk and the trunnion 130.

Cette réalisation permet notamment de ne pas avoir à enlever le stator lors du montage ou du démontage du disque DD1. Sinon, le procédé de montage et de démontage correspondent à ceux décrits précédemment.This embodiment makes it possible in particular not to have to remove the stator during assembly or disassembly of the DD1 disk. Otherwise, the assembly and disassembly procedure corresponds to those previously described.

De manière générale, les premiers moyens de fixation de l'ensemble tourillon/disque D2 sont plus courts que les seconds moyens de fixation permettant de fixer le premier anneau circulaire à l'ensemble tourillon/disque D2.In general, the first fastening means of the trunnion / disc D2 assembly are shorter than the second fixing means for fixing the first ring circular to the trunnion / disc D2 assembly.

L'invention permet ainsi de remplacer sans maintenance particulière ni perte de temps, le disque monobloc aubagé, pièce la plus soumise aux problèmes en service et ayant le plus d'impact sur les performances du compresseur.The invention thus makes it possible to replace without particular maintenance or loss of time, the bladed monoblock disc, the most problematic part in service and having the most impact on compressor performance.

L'invention ne se limite pas à une liaison boulonnée entre un disque, première pièce de rotor et un ensemble fixé de deuxième et troisième pièces de rotor mais peut s'étendre à toute pièce nécessitant le démontage séparé d'avec un ensemble de pièces fixées entre-elles.The invention is not limited to a bolted connection between a disk, the first rotor part and a fixed set of second and third rotor pieces but can extend to any piece requiring separate disassembly with a set of parts fixed together.

L'invention ne se limite pas non plus aux modes de réalisation de dispositif de fixation décrits ci-avant, seulement à titre d'exemple, mais elle englobe toutes les variantes que pourra envisager l'homme de l'art dans le cadre des revendications ci-après.The invention is not limited either to embodiments of fastening device described above, only as an example, but it encompasses all the variants that may consider those skilled in the art within the scope of the claims below.

Claims (12)

Pièce (D1) pour rattachement à l'entrée d'un rotor de compresseur, cette pièce (D1) étant apte à constituer une première pièce d'un rotor de compresseur, caractérisé en ce que la pièce (D1) est terminée par un premier anneau (12) muni d'une succession de trous (14) et d'encoches (16) et en ce que l'axe du premier anneau est apte à être centré sur l'axe de rotation (B) du rotor de compresseur pour rattachement à l'entrée du rotor de compresseur, le premier anneau (12) est apte à être placé contre une deuxième pièce (30) à symétrie de révolution du rotor fixée à une troisième pièce (D2) à symétrie de révolution du rotor par des moyens de fixation et formant un ensemble deuxième/troisième pièces du rotor, les encoches (16) étant aptes à contourner les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor, les trous (14) du premier anneau (12) étant aptes à être placés en vis à vis de trous de l'ensemble deuxième/troisième pièces pour fixation du premier anneau (12) à l'ensemble deuxième/troisième pièces.Part (D1) for attachment to the inlet of a compressor rotor, this part (D1) being able to form a first part of a compressor rotor, characterized in that the part (D1) is terminated by a first ring (12) provided with a succession of holes (14) and notches (16) and in that the axis of the first ring is adapted to be centered on the axis of rotation (B) of the compressor rotor for attached to the inlet of the compressor rotor, the first ring (12) is adapted to be placed against a second part (30) with symmetry of revolution of the rotor fixed to a third part (D2) with symmetry of revolution of the rotor by fastening means and forming a set second / third parts of the rotor, the notches (16) being able to bypass the fixing means of the assembly second / third parts of the rotor, the holes (14) of the first ring (12) being adapted to be placed opposite holes in the second / third piece assembly s for attaching the first ring (12) to the second / third piece assembly. Pièce selon la revendication 1, caractérisé en ce que le premier anneau (12) est dans un plan perpendiculaire à l'axe de rotation (B) du rotor.Part according to claim 1, characterized in that the first ring (12) is in a plane perpendicular to the axis of rotation (B) of the rotor. Pièce selon l'une des revendications 1 et 2, caractérisé en ce qu'elle comprend un disque (D1) et des aubes attachées sur sa périphérie.Part according to one of claims 1 and 2, characterized in that it comprises a disk (D1) and blades attached on its periphery. Pièce selon l'une des revendications précédentes, caractérisé en ce qu'elle comprend un disque (D1) muni d'une bride (10) reliée au premier anneau (12), la bride (10) et l'anneau (12) étant placés en aval du disque (D1) de façon que la fixation du disque (D1) avec l'ensemble deuxième/troisième pièces puisse s'effectuer en aval du disque (D1) par rapport au sens d'écoulement du flux dans le compresseur.Part according to one of the preceding claims, characterized in that it comprises a disk (D1) provided with a flange (10) connected to the first ring (12), the flange (10) and the ring (12) being placed downstream of the disk (D1) so that the attachment of the disk (D1) with the second / third parts assembly can be performed downstream of the disk (D1) relative to the flow direction of the flow in the compressor. Liaison entre une première pièce (D1), selon l'une des revendications 1 à 4, terminée par un premier anneau (12) muni d'une succession de trous (14) et d'encoches (16), l'axe du premier anneau (12) étant centré sur l'axe de rotation (B) du rotor de compresseur pour rattachement à l'entrée du rotor de compresseur, et un ensemble d'une deuxième pièce (30) de rotor fixée à une troisième (D2) pièce de rotor, la deuxième pièce (30) formant l'entrée du rotor de compresseur et étant terminée en aval par un deuxième anneau (32) comprenant des trous, la troisième pièce (D2) étant terminée en amont par un troisième anneau (22) comprenant des trous, les deuxième et troisième anneaux étant disposés l'un contre l'autre, de manière à placer leurs trous en vis à vis, et étant fixés entre eux par des premiers moyens de fixation, le premier anneau (12) circulaire étant disposé en amont de et contre l'ensemble deuxième/troisième pièces de façon à ce que les encoches contournent les premiers moyens de fixation de l'ensemble deuxième/troisième pièces du rotor et à ce que au moins certains des trous (14) du premier anneau (12) soient en vis à vis de trous de l'ensemble deuxième/troisième pièces, des seconds moyens de fixation fixant le premier anneau circulaire à l'ensemble deuxième/troisième pièces.Connection between a first part (D1) according to one of Claims 1 to 4, completed by a first ring (12) provided with a succession of holes (14) and notches (16), the axis of the first ring (12) being centered on the axis of rotation (B) of the compressor rotor for attached to the inlet of the compressor rotor, and an assembly of a second part (30) rotor attached to a third (D2) rotor piece, the second piece (30) forming the inlet compressor rotor and being terminated downstream by a second ring (32) comprising holes, the third piece (D2) being terminated upstream by a third ring (22) comprising holes, the second and third rings being arranged one against the other, so as to place their holes facing each other, and being fixed between them by first means the first circular ring (12) being arranged upstream of and against the assembly second / third pieces so that the notches circumvent the first means securing the second / third rotor assembly and that at least some holes (14) of the first ring (12) are facing the holes of the assembly second / third parts, second fixing means fixing the first ring circular to the second / third set. Liaison selon la revendication 5, caractérisé en ce que les deuxième (32) et troisième (22) anneaux sont dans un plan perpendiculaire à l'axe de rotation (B) du rotor.Binding according to claim 5, characterized in that the second (32) and third (22) rings are in a plane perpendicular to the axis of rotation (B) of the rotor. Liaison selon l'une des revendications 5 à 6, caractérisé en ce que les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor sont plus courts que les moyens de fixation permettant de fixer le premier anneau à l'ensemble deuxième/troisième pièces.Binding according to one of claims 5 to 6, characterized in that the fastening means of the second / third rotor parts are shorter than the fixing means for fixing the first ring to the second / third set rooms. Liaison selon l'une des revendications 5 à 7, caractérisé en ce que les moyens de fixation comprennent des systèmes vis-écrou.Binding according to one of claims 5 to 7, characterized in that the fastening means comprise screw-nut systems. Liaison selon la revendication 8, caractérisé en ce que la vis du système vis-écrou est retenue par un jonc permettant à la vis de tenir en cas d'absence de l'écrou.Binding according to claim 8, characterized in that the screw of the screw-nut system is retained by a ring allowing the screw to hold in the absence of the nut. Turbomachine comprenant un compresseur haute-pression muni d'une liaison selon l'une des revendications 5 à 9.Turbomachine comprising a high-pressure compressor provided with a connection according to one Claims 5 to 9. Procédé de montage d'une liaison selon l'une des revendications 5 à 9 consistant à placer les deuxième (32) et troisième (22) anneaux circulaires l'un contre l'autre, de manière à placer leurs trous en vis à vis, à fixer ces deuxième (32) et troisième (22) anneaux entre eux par des premiers moyens de fixation traversant certains des trous, à placer dans les trous restant des seconds moyens de fixation aptes à fixer l'ensemble deuxième/troisième pièce à la première pièce, à placer le premier anneau (12) circulaire en amont de et contre l'ensemble deuxième/troisième pièce de façon à ce que les encoches contournent les moyens de fixation de l'ensemble deuxième/troisième pièces du rotor et à ce que certains des trous du premier anneau (12) soient traversés par les seconds moyens de fixation afin de fixer le premier anneau (12) circulaire à l'ensemble deuxième/troisième pièces.A method of mounting a link according to one of claims 5 to 9 consisting of place the second (32) and third (22) circular rings together, so that to place their holes opposite, to fix these second (32) and third (22) rings between them by first fixing means passing through some of the holes, to be placed in the holes remaining second fastening means capable of fixing the assembly second / third piece at the first piece, to place the first ring (12) circular upstream of and against the whole second / third piece so that the notches circumvent the means fixing the entire second / third rotor parts and that some of the holes the first ring (12) are traversed by the second fastening means in order to fix the first ring (12) circular to the set second / third pieces. Procédé de démontage d'une liaison selon l'une des revendications 5 à 9 consistant à défaire les seconds moyens de fixation pour enlever la première pièce du rotor de compresseur et conserver l'ensemble deuxième pièce/troisième pièce du rotor.Method for disassembling a connection according to one of claims 5 to 9 consisting in undo the second fastening means to remove the first piece of the rotor from compressor and keep the whole second piece / third piece of the rotor.
EP04291706A 2003-07-11 2004-07-06 Connection between rotor disks in a compressor Active EP1496266B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308556A FR2857419B1 (en) 2003-07-11 2003-07-11 IMPROVED CONNECTION BETWEEN DISCS AND ROTOR LINES OF A COMPRESSOR
FR0308556 2003-07-11

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JP (1) JP4146399B2 (en)
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Also Published As

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JP2005030398A (en) 2005-02-03
ES2297352T3 (en) 2008-05-01
FR2857419A1 (en) 2005-01-14
RU2004121113A (en) 2006-01-10
CA2472934A1 (en) 2005-01-11
EP1496266B1 (en) 2008-02-06
JP4146399B2 (en) 2008-09-10
US7210909B2 (en) 2007-05-01
CA2472934C (en) 2011-11-22
RU2279571C2 (en) 2006-07-10
FR2857419B1 (en) 2005-09-23
DE602004011643T2 (en) 2009-01-29
US20050025625A1 (en) 2005-02-03
DE602004011643D1 (en) 2008-03-20

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