EP1496266A1 - Verbindung zwischen Schaufelscheiben eines Verdichterrotors - Google Patents

Verbindung zwischen Schaufelscheiben eines Verdichterrotors Download PDF

Info

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
English (en)
French (fr)
Other versions
EP1496266B1 (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 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/de
Application granted granted Critical
Publication of EP1496266B1 publication Critical patent/EP1496266B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04291706A 2003-07-11 2004-07-06 Verbindung zwischen Schaufelscheiben eines Verdichterrotors Expired - Lifetime EP1496266B1 (de)

Applications Claiming Priority (2)

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

Publications (2)

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

Family

ID=33443277

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291706A Expired - Lifetime 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1584784A1 (de) 2004-04-09 2005-10-12 Snecma Einrichtung zur Montage von ringförmigen Flanschen, insbesondere in Turbomaschinen
WO2009144409A1 (fr) * 2008-05-29 2009-12-03 Snecma Bride annulaire de fixation d'un element de rotor ou de stator

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
GB2456520B (en) * 2008-01-16 2009-12-09 Rolls Royce Plc A turbomachinery disc
FR2931873B1 (fr) * 2008-05-29 2010-08-20 Snecma Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier,circuit de refroidissement d'un disque de turbine d'un tel ensemble.
EP2396376B1 (de) * 2009-02-13 2019-07-17 Avery Dennison Corporation Adhäsive verbindungen
FR2942854B1 (fr) * 2009-03-06 2014-07-04 Snecma Dispositif de reparation pour bride de carter de moteur aeronautique
US8769814B2 (en) * 2009-07-06 2014-07-08 United Technologies Corporation Device and method for repairing a forward frame V-blade in an aircraft engine
RU2453708C1 (ru) * 2010-12-22 2012-06-20 Открытое акционерное общество "Авиадвигатель" Ротор двухступенчатой турбины
RU2453709C1 (ru) * 2010-12-23 2012-06-20 Открытое акционерное общество "Авиадвигатель" Ротор турбины газотурбинного двигателя
US20130025290A1 (en) * 2011-07-29 2013-01-31 United Technologies Corporation Ingestion-tolerant low leakage low pressure turbine
US20130156584A1 (en) * 2011-12-16 2013-06-20 Carney R. Anderson Compressor rotor with internal stiffening ring of distinct material
RU2532390C1 (ru) * 2013-09-10 2014-11-10 Открытое акционерное общество "Авиадвигатель" Ротор турбины высокого давления
RU2564959C1 (ru) * 2014-10-14 2015-10-10 Открытое акционерное общество "Авиадвигатель" Газотурбинный двигатель
FR3057015B1 (fr) * 2016-09-30 2018-12-07 Safran Aircraft Engines Disque de rotor comportant une toile a epaisseur variable
DE102017205122A1 (de) 2017-03-27 2018-09-27 MTU Aero Engines AG Turbomaschinen-Bauteilanordnung
US10697300B2 (en) * 2017-12-14 2020-06-30 Raytheon Technologies Corporation Rotor balance weight system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1087100A2 (de) * 1999-09-23 2001-03-28 General Electric Company Kompressorrotor- Konfiguration
EP1122443A2 (de) * 2000-01-31 2001-08-08 General Electric Company Montage eines Rotors
US6499957B1 (en) * 1998-06-27 2002-12-31 Miu Aero Engines Gmbh Rotor for a turbomachine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5052891A (en) * 1990-03-12 1991-10-01 General Motors Corporation Connection for gas turbine engine rotor elements
US5211541A (en) * 1991-12-23 1993-05-18 General Electric Company Turbine support assembly including turbine heat shield and bolt retainer assembly
US5350278A (en) * 1993-06-28 1994-09-27 The United States Of America As Represented By The Secretary Of The Air Force Joining means for rotor discs
US5388963A (en) * 1993-07-02 1995-02-14 United Technologies Corporation Flange for high speed rotors

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6499957B1 (en) * 1998-06-27 2002-12-31 Miu Aero Engines Gmbh Rotor for a turbomachine
EP1087100A2 (de) * 1999-09-23 2001-03-28 General Electric Company Kompressorrotor- Konfiguration
EP1122443A2 (de) * 2000-01-31 2001-08-08 General Electric Company Montage eines Rotors

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1584784A1 (de) 2004-04-09 2005-10-12 Snecma Einrichtung zur Montage von ringförmigen Flanschen, insbesondere in Turbomaschinen
WO2009144409A1 (fr) * 2008-05-29 2009-12-03 Snecma Bride annulaire de fixation d'un element de rotor ou de stator
FR2931869A1 (fr) * 2008-05-29 2009-12-04 Snecma Bride annulaire de fixation d'un element de rotor ou de stator
US9039351B2 (en) 2008-05-29 2015-05-26 Snecma Annular flange for fastening a rotor or stator element

Also Published As

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

Similar Documents

Publication Publication Date Title
EP1496266B1 (de) Verbindung zwischen Schaufelscheiben eines Verdichterrotors
EP2414638B1 (de) Turbinenrad mit schaufeln unterschiedlicher eigenfrequenz und dämpfungsvorrichtung
CA2387462C (fr) Dispositif de prelevement d'air par ecoulement centripete
EP1918512B1 (de) Ausgleichssystem für einen Strömungsmaschinenrotor
EP1811131B1 (de) Anordnung von Statorsektoren für einen Verdichter eines Turbotriebwerks
EP2315642B1 (de) Verfahren zum reparieren oder nachbearbeiten einer turbomaschinenrotor
EP1406019B1 (de) Trommelrotor für eine Turbomaschine
EP2366061B1 (de) Turbinenrad mit einem axialrückhaltesystem für schaufeln
CA2824379C (fr) Rotor de soufflante et turboreacteur associe
EP2469100B1 (de) Motorkompressor mit Drehkupplung in einer Hohlwelle des Kompressors
FR2930595A1 (fr) Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
FR2997444A1 (fr) Moyeu de carter pour une turbomachine
FR3010442A1 (fr) Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef
EP2603670B1 (de) Vorrichtung zur arretierung eines fusses einer laufschaufel
FR2978798A1 (fr) Secteur angulaire de redresseur de turbomachine a amortissement des modes de vibrations
FR2974863A1 (fr) Disque de soufflante de turbomachine
FR3072607A1 (fr) Turbomachine comprenant un ensemble de redressement
FR2907496A1 (fr) Disque de rotor de turbomachine et module de turbomachine comprenant un tel disque
CA2577502A1 (fr) Roue de rotor de turbomachine
FR3078100A1 (fr) Couronne aubagee pour stator de turbomachine dont les aubes sont reliees a la virole externe par appui conique et pion frangible
EP3420198A1 (de) Gleichrichter für turbomaschinenverdichter eines flugzeugs mit luftabsaugungsöffnungen mit gestreckter form im umfangsrichtung
FR2948737A1 (fr) Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
FR2983924A1 (fr) Carter annulaire pour un compresseur de turbomachine
EP1310633B1 (de) Leitschaufelstufe eines Verdichters und Verdichter beinhaltend so eine Leitschaufelstufe
FR3102205A1 (fr) Rotor de turbomachine à masselotte

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

17P Request for examination filed

Effective date: 20041228

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

17Q First examination report despatched

Effective date: 20060313

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602004011643

Country of ref document: DE

Date of ref document: 20080320

Kind code of ref document: P

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2297352

Country of ref document: ES

Kind code of ref document: T3

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20081107

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

Ref country code: ES

Payment date: 20120716

Year of fee payment: 9

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130707

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

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

Ref country code: IT

Payment date: 20230620

Year of fee payment: 20

Ref country code: FR

Payment date: 20230621

Year of fee payment: 20

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

Ref country code: SE

Payment date: 20230622

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20230620

Year of fee payment: 20

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

Ref country code: DE

Payment date: 20230620

Year of fee payment: 20