EP1496266B1 - Verbindung zwischen Schaufelscheiben eines Verdichterrotors - Google Patents

Verbindung zwischen Schaufelscheiben eines Verdichterrotors Download PDF

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Publication number
EP1496266B1
EP1496266B1 EP04291706A EP04291706A EP1496266B1 EP 1496266 B1 EP1496266 B1 EP 1496266B1 EP 04291706 A EP04291706 A EP 04291706A EP 04291706 A EP04291706 A EP 04291706A EP 1496266 B1 EP1496266 B1 EP 1496266B1
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EP
European Patent Office
Prior art keywords
ring
rotor
holes
assembly
compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP04291706A
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English (en)
French (fr)
Other versions
EP1496266A1 (de
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 SAS
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Publication date
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Publication of EP1496266A1 publication Critical patent/EP1496266A1/de
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Publication of EP1496266B1 publication Critical patent/EP1496266B1/de
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 to the connection between the bladed disc of the first stage of the rotor of the compressor and the bladed disc of the second stage of the rotor of the compressor.
  • the compressor receives the inlet air flow.
  • the bladed disc at the inlet of the compressor is likely to receive foreign bodies such as ice cubes, birds or others.
  • the first is thus the most exposed to damage by foreign bodies. Therefore, 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 comprising different parts causes balancing and alignment operations that require a passage to qualified and equipped maintenance workshop. During these disassembly operations, it is important that the rotor line is not broken.
  • the present invention improves the situation.
  • the invention relates to a connection between a first piece for attachment to the inlet of a compressor rotor, and an assembly of a second rotor part forming the inlet of the compressor rotor and attached to a third rotor part.
  • the piece is terminated by a first ring provided with a succession of holes and notches.
  • the first piece is terminated by a first ring provided with a succession of holes and notches, and the axis of the first ring is centered on the axis of rotation of the compressor rotor for attachment to the inlet of the compressor rotor
  • the second piece is terminated downstream by a second ring comprising holes
  • the third piece is completed upstream by a third ring comprising holes
  • the second and third rings being arranged one against the other, so as to place their holes opposite, and being fixed between them by first fixing means.
  • the first ring is disposed upstream of and against the second / third parts assembly so that the notches bypass the first fastening means of the second / third rotor assembly and that the at least some of the holes of the first ring are opposite holes in the second / third parts assembly, second fastening means fixing the first circular ring to the second / third parts assembly.
  • 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 disc 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 second / third parts set is downstream. of the disk with respect to the flow direction of the flow in the compressor.
  • the second and third rings are in a plane perpendicular to the axis of rotation of the rotor.
  • the securing means of the second / third rotor assembly are shorter than the fixing means for fixing the first ring to the second / third parts assembly.
  • fastening means comprise screw-nut systems.
  • the screw of the screw-nut system is retained by a ring allowing the screw to hold in the absence of the nut.
  • the invention relates in particular to a turbomachine comprising a high-pressure compressor provided with a connection as described above.
  • the invention further relates to a method of mounting a connection as described above, consisting of placing the second and third circular rings against each other, so as to place their holes opposite, to fix these second and third rings between them by first fastening means passing through some of the holes, to be placed in the remaining holes of the second fastening means adapted to fix the second / third piece assembly to the first piece, to place the first circular ring upstream of and against the second / third piece assembly so that the notches bypass the securing means of the assembly second / third rotor parts and that some of the holes of the first ring are traversed by the second fastening means in order to attach the first circular ring to the second / third piece assembly.
  • the invention further relates to a method of disassembling a connection as described above, consisting of undoing the second fastening means to remove the first piece of the compressor rotor and keep the assembly second piece / third piece of the rotor.
  • FIG. 1 shows a partial section of the rotor part of a turbojet high-pressure compressor composed of different compression stages E1 to E5, each comprising a disk D1 to D5 provided with an impeller ring A1 to A5.
  • Each compression stage is also composed, downstream of each blisk, of a flow rectifier not shown 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 stator part of the compressor delimit a "vein" for the flow of air to be compressed.
  • a rotor line is used to denote the continuous outer surface of the rotor forming the lower limit of this vein.
  • the bladed disks D2 to D5 of the compressor are formed in one piece called a set of disks.
  • the bladed disk D1 is advantageously a one-bladed blisk attached to the rotor upstream of the set of discs so that it can be easily removed for maintenance and maintenance purposes.
  • This first monobloc bladed disk constituting the first stage of the high-pressure compressor is capable of receiving foreign bodies such as ice cubes, birds or others.
  • the rotor part of the compressor is rotated by a shaft S itself driven in rotation by a turbine located downstream of the compressor. The axis of rotation is noted B.
  • 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” or “outer” denomination of the rings (or part of a ring) ending in a piece is to be interpreted as rings extending towards the interior of the piece, namely rings leaving the piece and having a radius decreases, respectively rings extending outwardly of the piece, 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 inlet of the compressor, a trunnion 30 of flared shape terminated by a radial ring 32.
  • the disk D2 comprises an upstream flange 20 extending in the direction of the trunnion and ending in a radial ring 22 whose surface upstream comes into contact with the downstream surface of the radial ring 32 of the pin.
  • the one-piece blisk D1 comprises a downstream flange 10 extending towards the radial ring 32 of the trunnion and ending in a radial ring 12 whose downstream surface comes into contact with the upstream surface of the radial ring 32.
  • blisk D1 the pin 30 and the disk D2 are connected to each other by a fastening means such as a screw-nut system 40 shown in Figure 2 passing through holes opposite the rings 12, 32 and 22
  • the downstream flange 10 with a symmetry of revolution of the blisk D1 allows a downstream connection of this disc with the rotor to meet the criteria of resistance to vibration, durability, and resistance to the loss of blades. this disk of the first stage of compression.
  • 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 monoblock disc D1 without blade, this disc being able to receive blades.
  • This first piece of the rotor comprises a circular foot 11 surmounted by a circular plate 18 adapted to receive blades.
  • the circular foot 11 comprises the circular downstream flange 10 extending by way of example in the direction of the axis of rotation B and ending in 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 radial ring 12 is an outer ring.
  • FIG. 4 shows 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 ending downstream by a radial ring 32.
  • This radial ring is composed of an inner radial portion 35 called foot and an outer radial portion terminated by a flange 38 extending axially upstream and downstream.
  • the outer radial portion comprises holes 34 intended to be brought into contact with the holes and the notches of the outer radial ring 12 of the upstream disk D1 on the side of the upstream surface of the radial ring 32 and with the holes of FIG. the radial ring 22 of the downstream disk D2 on the side of the downstream surface 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 circular downstream flange 20 tightening upstream in frustoconical form and ending in the radial ring 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 so as to reduce the amount of material of the radial ring 22. These notches also serve as means for indicating the position of the holes 24.
  • Figures 6 and 7 show the steps of mounting a connection according to the invention.
  • the journal in a first step, is connected to the disk D2 by positioning the downstream surface of the outer radial ring 32 against the upstream surface of the internal radial ring 22 of the downstream disk D2 while screws the holes of the outer radial ring 32 and the holes of the inner radial ring 22.
  • the first fastening means such as screw / nut systems, are set up in some of the holes facing each other, these holes being detectable from the notches 26 of the inner radial ring 22 for example.
  • these marked holes correspond to the central holes of the set of holes located between two notches 26 by way of example.
  • the marked holes must correspond to the distribution of the notches 16 of the disk D1 for the reasons developed below.
  • the rotor line is continuous even in the absence of upstream disk D1, in other words, the vein of the air flow is maintained.
  • the pin 30 and the disk D2 form an assembly fixed by the first fastening means, this assembly is called the second / third rotor assembly.
  • the remaining holes are provided with a part of second fastening means, for example 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 of the rod the screw extending substantially on the side of the upstream surface of the outer radial ring 32 of the pin 30 so as to receive the thickness of the outer radial ring 12 of the disk D1 and the fixing nut.
  • the screws of the second fastening means are retained by a ring thus avoiding the screws out of the holes when the nuts are not yet engaged on the screw rods.
  • Nuts are screwed onto the ends of the screws and are clamped against the upstream surface of the outer radial ring 12 of the disk D1.
  • the axial flange 38 of the outer radial ring 32 of the trunnion covers upstream the radial outer edge of the outer radial ring 12 of the disk D1, and downstream the radial outer edge of the internal radial ring 22 of the disk D2. .
  • the axial flange 38 thus makes it possible to exert a centripetal radial force on the external radial ring 12 of the disk D1 and on the internal radial ring 22 of the disk D2, in particular during operation.
  • the disassembly of the connection between the disk D1 and the trunnion / disk assembly D2 is carried out as follows.
  • the stator is partly removed to be able to access 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 removed by axial traction upstream. It remains the pin and the disk D2 fixed together by the first fastening means, for example by eight screw-nut systems, and it also remains the ends of the screw rods of the second fixing means retained by the rods.
  • the monoblock disk D1 can be removed from the rotor with great ease and without having to break the rotor line.
  • the monoblock disk D1 can be repaired or replaced by another monoblock disk D1 in good condition.
  • the mounting of this disk D1 is effected as stated above by matching the notches 16 with the first fastening means and the holes 14 with a portion of the second fastening means, namely the screw rods.
  • connection is performed without the presence of the stator which is disposed after implementation of the connection.
  • a variant of this embodiment would allow mounting of the connection with the presence of the stator: screw / nut systems must then be reversed (the nut being located instead of the head of the screw and vice versa).
  • FIG. 8 represents an alternative embodiment of the connection according to the invention.
  • the disk DD1 consists of a flange 110 extending axially in a slightly inclined manner and terminating in an internal radial ring 112 adapted to be placed against the upstream surface of the outer radial ring 132 of the trunnion 130.
  • ring 112 comprises a succession of holes and notches such as ring 12.
  • Disk DD2 is the same as disk D2 and its inner radial ring 122 is adapted 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 DD1 disk comprises a shortened foot compared to the previous embodiment of the disk D1 so that it is possible to access the fastening means 140, similar to the fastening means 40 of the previous embodiment, by a passage between the foot of the disk DD1 and the trunnion 130.
  • This embodiment makes it possible in particular not to have to remove the stator during assembly or disassembly of the disk DD1. Otherwise, the method of assembly and disassembly correspond to those described above.
  • the first fixing means of the trunnion / disc D2 assembly are shorter than the second fixing means for fixing the first circular ring to the trunnion / disk D2 assembly.
  • the invention thus makes it possible to replace, without particular maintenance or loss of time, the bladed monobloc disc, the part most subjected to problems in service and having the greatest impact on the performance of the compressor.
  • the invention is not limited to a bolted connection between a disc, a first rotor part and a fixed assembly of second and third rotor parts but may extend to any part requiring separate disassembly from a set of fixed parts. between them.

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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)

Claims (11)

  1. Verbindung zwischen einem ersten Teil (D1) zur Befestigung am Eintritt eines Verdichterrotors und einer Gesamtanordnung eines zweiten Rotorteils (30), das den Eintritt des Verdichterrotors bildet und an einem dritten Rotorteil (D2) befestigt ist, wobei das erste Teil (D1) mit einem ersten Ring (12) endet, der mit einer Aufeinanderfolge von Löchern (14) und Einschnitten (16) versehen ist, und wobei die Achse des ersten Rings (12) zur Befestigung am Eintritt eines Verdichterrotors auf der Drehachse (B) des Verdichterrotors zentriert ist, wobei das zweite Teil (30) hinten mit einem zweiten Ring (32) endet, der Löcher enthält, wobei das dritte Teil (D2) vom mit einem dritten Ring (22) endet, der Löcher enthält, wobei der zweite und der dritte Ring aneinander angeordnet sind, so dass ihre Löcher sich einander gegenüber befinden, und durch erste Befestigungsmittel aneinander befestigt sind,
    dadurch gekennzeichnet,
    dass der erste Ring (12) vor und an der Gesamtanordnung des zweiten und des dritten Teils dergestalt angeordnet ist, dass die Einschnitte um die ersten Befestigungsmittel der Gesamtanordnung des zweiten und des dritten Rotorteils herum verlaufen und dass wenigstens einige Löcher (14) des ersten Rings (12) den Löchern der Gesamtanordnung des zweiten und des dritten Teils gegenüber liegen, wobei zweite Befestigungsmittel den ersten, kreisförmigen Ring an der Gesamtanordnung des zweiten und des dritten Teils befestigen.
  2. Verbindung nach Anspruch 1,
    dadurch gekennzeichnet,
    dass der erste Ring (12) sich in einer Ebene befindet, die im rechten Winkel zur Drehachse (B) des Rotors verläuft.
  3. Verbindung nach einem der Ansprüche 1 und 2,
    dadurch gekennzeichnet,
    dass sie eine Scheibe (D1) und an deren Außenumfang befestigte Schaufeln umfasst
  4. Verbindung nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass sie eine Scheibe (D1) umfasst, die mit einer Schelle (10) versehen ist, welche mit dem ersten Ring (12) verbunden ist, wobei die Schelle (10) und der Ring (12) hinter der Scheibe (D1) angeordnet sind, so dass die Befestigung der Scheibe (D1) mit der Gesamtanordnung des zweiten und des dritten Teils hinter der Scheibe (D1) erfolgt, bezogen auf die Strömungsrichtung des Stroms im Verdichter.
  5. Verbindung nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass der zweite Ring (32) und der dritte Ring (22) sich in einer Ebene befinden, die im rechten Winkel zur Drehachse (B) des Rotors verläuft.
  6. Verbindung nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass die Befestigungsmittel der Gesamtanordnung des zweiten und des dritten Teils des Rotors kürzer sind als die Befestigungsmittel zur Befestigung des ersten Rings an der Gesamtanordnung des zweiten und des dritten Teils.
  7. Verbindung nach einem der vorherigen Ansprüche,
    dadurch gekennzeichnet,
    dass die Befestigungsmittel Schrauben-Mutter-Systeme umfassen.
  8. Verbindung nach Anspruch 7,
    dadurch gekennzeichnet,
    dass die Schraube des Schrauben-Mutter-Systems durch einen Ring festgehalten wird, durch den die Schraube Halt findet, wenn keine Mutter aufgeschraubt ist.
  9. Turbomaschine mit einem Hochdruckverdichter, der mit einer Verbindung nach einem der vorherigen Ansprüche versehen ist.
  10. Verfahren zum Einbau einer Verbindung nach einem der Ansprüche 1 bis 8, welches darin besteht, den kreisförmigen zweiten Ring (32) und dritten Ring (22) dergestalt aneinander zu legen, dass ihre Löcher sich einander gegenüber befinden, diesen zweiten Ring (32) und dritten Ring (22) durch erste Befestigungsmittel, die durch einige der Löcher hindurch verlaufen, aneinander zu befestigen, in die übrigen Löcher zweite Befestigungsmittel einzubringen, die geeignet sind, die Gesamtanordnung des zweiten und des dritten Teils an dem ersten Teil zu befestigen, den ersten kreisförmigen Ring (12) vor und an der Gesamtanordnung des zweiten und des dritten Teils dergestalt anzuordnen, dass die Einschnitte um die Befestigungsmittel der Gesamtanordnung des zweiten und des dritten Rotorteils herum verlaufen und dass die zweiten Befestigungsmittel einige der Löcher des ersten Rings (12) hindurch verlaufen, um den ersten kreisförmigen Ring (12) an der Gesamtanordnung des zweiten und des dritten Teils zu befestigen.
  11. Verfahren zum Ausbau einer Verbindung nach einem der Ansprüche 1 bis 8, welches darin besteht, die zweiten Befestigungsmittel zu lösen, um das erste Teil des Verdichterrotors abzunehmen und die Gesamtanordnung des zweiten und des dritten Rotorteils dabei zu bewahren.
EP04291706A 2003-07-11 2004-07-06 Verbindung zwischen Schaufelscheiben eines Verdichterrotors Active EP1496266B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308556A FR2857419B1 (fr) 2003-07-11 2003-07-11 Liaison amelioree entre disques aubages sur la ligne rotor d'un compresseur
FR0308556 2003-07-11

Publications (2)

Publication Number Publication Date
EP1496266A1 EP1496266A1 (de) 2005-01-12
EP1496266B1 true EP1496266B1 (de) 2008-02-06

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EP04291706A Active EP1496266B1 (de) 2003-07-11 2004-07-06 Verbindung zwischen Schaufelscheiben eines Verdichterrotors

Country Status (8)

Country Link
US (1) US7210909B2 (de)
EP (1) EP1496266B1 (de)
JP (1) JP4146399B2 (de)
CA (1) CA2472934C (de)
DE (1) DE602004011643T2 (de)
ES (1) ES2297352T3 (de)
FR (1) FR2857419B1 (de)
RU (1) RU2279571C2 (de)

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Publication number Priority date Publication date Assignee Title
FR2868814B1 (fr) 2004-04-09 2009-12-18 Snecma Moteurs Dispositif d'assemblage de brides annulaires, en particulier dans une turbomachine
FR2875535B1 (fr) * 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
FR2875534B1 (fr) * 2004-09-21 2006-12-22 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc
FR2885167B1 (fr) * 2005-04-29 2007-06-29 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
DE102007031712A1 (de) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung und Verfahren zum Einspannen von beschaufelten Rotorscheiben eines Strahltriebwerkes
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FR2931869B1 (fr) * 2008-05-29 2014-12-12 Snecma Bride annulaire de fixation d'un element de rotor ou de stator
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JP2005030398A (ja) 2005-02-03
DE602004011643D1 (de) 2008-03-20
US7210909B2 (en) 2007-05-01
JP4146399B2 (ja) 2008-09-10
RU2004121113A (ru) 2006-01-10
DE602004011643T2 (de) 2009-01-29
RU2279571C2 (ru) 2006-07-10
US20050025625A1 (en) 2005-02-03
EP1496266A1 (de) 2005-01-12
FR2857419B1 (fr) 2005-09-23
CA2472934A1 (fr) 2005-01-11
CA2472934C (fr) 2011-11-22
FR2857419A1 (fr) 2005-01-14
ES2297352T3 (es) 2008-05-01

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