EP1498579B1 - Rotorscheibe mit einem ringförmigen Flansch - Google Patents

Rotorscheibe mit einem ringförmigen Flansch Download PDF

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Publication number
EP1498579B1
EP1498579B1 EP04291803.7A EP04291803A EP1498579B1 EP 1498579 B1 EP1498579 B1 EP 1498579B1 EP 04291803 A EP04291803 A EP 04291803A EP 1498579 B1 EP1498579 B1 EP 1498579B1
Authority
EP
European Patent Office
Prior art keywords
collar
diameter
flange
ring
foot
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
EP04291803.7A
Other languages
English (en)
French (fr)
Other versions
EP1498579A1 (de
Inventor
Kamel Benderradji
Marc Marchi
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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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1498579A1 publication Critical patent/EP1498579A1/de
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Publication of EP1498579B1 publication Critical patent/EP1498579B1/de
Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a device for retaining an annular flange against a radial face of a disk and rotor.
  • It relates more specifically to a device for retaining an annular flange against a radial face of a rotor disk, said disk having in said radial face an annular recess delimited by a plurality of walls, one of which is formed by the inner face of a flange.
  • said flange having, in its radially inner portion, an annular base bearing against the radially outer wall of the recess and a foot which extends radially inwards in the recess from the base, said device comprising a split annular retaining ring disposed in the recess, this ring having a first radial surface abutting against the inner face of the flange, a second radial surface abutting against the axially outer face foot and a peripheral surface abutting against said foot or said base.
  • the flange is provided to prevent the axial displacement of fir-tree type blades whose feet are mounted in axial slots provided at the periphery of the rotor disc.
  • the annular ring is firstly slotted in the recess of the disc, then it is compressed radially towards the inside of the recess by means of tools pressing on the peripheral wall of the ring until these tools come to press the flange of the disc. Then, the base of the flange is slid along the radially outer wall of the recess.
  • the ring has at its axially inner end a peripheral rabbet in which is housed the radially inner portion of the foot.
  • the outer diameter of the ring is smaller than the inside diameter of the base of the flange to allow the release of the compression tools during assembly and their introduction during a possible disassembly.
  • the diameter of the bore of the flange foot is greater than diameter of the flange to allow the introduction of the inner portion of the flange in the recess around the compression tools bearing against the periphery of the flange.
  • the flange being subjected to axial stresses during impacts on the blades as a result of the ingestion of debris, which are taken up by the retaining ring, shearing moments occur on the ring due to differences in diameter between the bore of the foot and the flange.
  • the manufacture of this ring requires expensive machining.
  • FR 2 812 906 has proposed a modified retaining ring which has at the periphery of its outer radial face a chamfer which allows the automatic compression of said ring during the passage of the foot of the flange during assembly.
  • This foot has notches to allow the introduction of compression tools of the ring for disassembly.
  • This ring is also massive and requires expensive machining.
  • the retaining ring remains in the recess during disassembly of the flange for repair or replacement of a blade for example.
  • This ring is thus different from a traditional circlip that is expanded by means of a piece for its establishment around a tree and which retracts elastically in a groove formed at the periphery of the shaft.
  • the object of the invention is to provide a system for axial retention of a rotor disc flange which is simple to produce and inexpensive and which facilitates the assembly of parts.
  • the ring is constituted by a rod interposed axially between the foot of the flange and the flange, and whose peripheral surface is in abutment against the base, said peripheral surface and said flange having in correspondence with notches opening outwardly and intended to receive compression tools of said rod which retract into the contour of the flange during assembly or disassembly of said flange.
  • the foot of the flange has a bore whose diameter is substantially equal to the diameter of the flange.
  • the radially inner portion of the ring is housed in a groove formed behind the flange.
  • This groove preferably has a U-shaped section and the ring has opposite planar radial faces.
  • the axial width of the groove is equal to or slightly greater than the thickness of the ring.
  • the drawings show a turbomachine disk 1 which comprises at its periphery a plurality of substantially axial cells 2 intended to receive blade roots 3 which extend radially outwards. These vanes are immobilized axially at least on one face 4 of the disk 1 by an annular flange 5 whose radially inner portion 6 is housed in an annular recess 7 formed in the face 4 and is immobilized therein by a retaining ring which, according to FIG. invention, is in the form of a snap ring 8.
  • the terms “inner” and “outer” mean a wall or surface respectively close to or distant from the axis of rotation of the disk, and the terms “inner” and “outer” refer to a wall or a surface respectively near or far from the median plane of disk 1.
  • the annular recess 7 is delimited radially on the outside by a substantially cylindrical wall 9 connected by a concave surface 10a an annular groove 12, of U-shaped section, disposed behind a flange 13 which extends radially outwards and of which the diameter is slightly greater than the diameter of the shoulder 14 formed by the concave surface 10 and the internal axial face of the groove 12.
  • the radially inner portion 6 of the flange 5 has a base 15 which extends into the recess 7 and which has a cylindrical peripheral surface 15a which bears against the cylindrical wall 9, and a foot 16 placed under the base 15 and which extends radially inwards.
  • the diameter of the bore 17 of the foot 16 is substantially equal to or slightly greater than the diameter of the flange 13, in order to allow the insertion of the radially inner portion 6 of the flange 5 into the recess 7 during assembly, or its extraction. for the purposes of repair or maintenance of the blades 3.
  • the outer face 18 of the foot 16 is disposed in a radial plane passing through the groove 12 in the vicinity of the shoulder 14. This face 18 is connected to the radially inner face of the the base 15, and forms with the latter a rabbet 19.
  • rabbet 19 houses the radially outer portion of the rod 8, the radially inner portion of which partially fits into the groove 12.
  • the ring 8 has two parallel axial faces perpendicular to the axis of rotation of the disk 1, namely an outer axial face 20 bearing against the inner face of the flange 13 and an inner axial face 21 bearing against the outer face 18 of the foot 16 and its peripheral surface 22 bears against the radially inner face of the base 15.
  • the rod 8 is retracted into the groove 12 by means of compression tools.
  • the flange 13 and the periphery of the ring 8 have correspondingly a plurality of notches 30a on the flange 13 and 30b on the rod 8, in which the claws 25 of the compression tools are positioned, these claws being dimensioned in such a way that when the ring 8 is retracted, the walls defining the pairs of notches 30a and 30b being aligned, the claws 25 retract into the diameter or the contour of the flange 13 and are then positioned in the geometric cylinder defined by the bore 17 of the foot 16.
  • the depth of the groove 7 is calculated to allow the retraction of the claws 25, during the compression of the rod 8.
  • the rod 8 Before placing the flange 5, the rod 8 is introduced into the recess 7, its radially inner portion preferably being in the groove 12, as shown in FIG. figure 3 .
  • the claws 25 of the compression tool are spread outward and are arranged in the notches 30b of the ring 8.
  • the claws 25 are brought towards the axis of rotation of the disc 1 by clamping, which compresses the ring 8 which retracts into the groove 7.
  • the flange 5 When the claws 25 bear against the notches 30a of the flange 13, as shown in FIG. figure 4 , the flange 5 is brought closer to the disc 1 and the foot 16 is passed over the flange 13, the ring 8 and the claws 25. The flange 5 is then pressed against the axial face 4, applying pressure to it. axial F then remove the claws 25, as shown by an arrow on the figure 5 . The ring 8 then expands and its periphery 22 bears against the base 15. The axial pressure F exerted on the flange 5 is suppressed, and the ring 8 is then compressed between the foot 16 and the flange 13, as well as that is shown on the figure 6 . Disassembly of the flange 5 is done by the reverse process.
  • the diameter of the shoulder 14 may be equal to the diameter of the flange 13. But advantageously, the diameter of the shoulder 14 is at most equal to the diameter of the bottom of the notches 30a of the flange 13. This arrangement allows the claws 25 of extend above the shoulder 14, during the compression of the rod 8 without impeding the mounting of the flange 5.
  • the inner diameter of the rod 8, which is not subject to stress, is preferably smaller than the diameter of the shoulder 14, so that the rod 8 is correctly positioned relative to the groove when the claws 25 are placed in the notches. 30b of the ring 8.
  • the rod 8 which is in the form of a split washer, is easy to manufacture and inexpensive.
  • the volume of the recess 7 can be limited to the maximum, which reinforces the periphery of the disc 1 which, in general, is subjected to considerable centrifugal forces.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
  • Rotary Pumps (AREA)

Claims (7)

  1. Rotorscheibe, die mit Zellen, welche dazu bestimmt sind, Schaufeln aufzunehmen, versehen ist, die einen ringförmigen Flansch (5) trägt, der an einer Radialfläche (4) der Scheibe angebracht ist, um die Schaufeln zu halten, wobei die Scheibe in der Radialfläche eine ringförmige Ausnehmung (7) aufweist, die durch mehrere Wände begrenzt ist, von denen eine durch die Innenseite eines Stegs (13), der sich radial nach außen erstreckt, gebildet ist, und wobei der Flansch (5) in seinem radial inneren Teil eine ringförmige Basis (15) in Anlage an der radial äußeren Wand (9) der Ausnehmung (7) sowie einen Fuß (16), der sich in der Ausnehmung (7) von der Basis (15) aus radial nach innen erstreckt, aufweist, wobei ein ringförmiger, geschlitzter Haltering in der Ausnehmung (7) angeordnet ist, wobei dieser Ring eine erste Radialfläche in Anlage an der Innenseite des Stegs, eine zweite Radialfläche in Anlage an der axial äußeren Seite des Fußes und eine Umfangsfläche in Anschlag an dem Fuß oder der Basis aufweist,
    dadurch gekennzeichnet, dass der Ring durch einen Reif (8), der zwischen dem Fuß (16) des Flansches (5) und dem Steg (13) axial eingefügt ist und dessen Umfangsfläche (22) an der Basis (15) in Anschlag ist, gebildet ist, dass die Umfangsfläche (22) und der Steg (13) übereinstimmend Kerben (30a, 30b) umfassen, welche radial nach außen münden und dazu bestimmt sind, Werkzeuge zum Zusammendrücken (25) des Reifs (8) aufzunehmen, die bei der Montage oder der Demontage des Flansches (5) im Wesentlichen vollständig in der Kontur des Stegs (13) verschwinden, und dass der Fuß (16) des Flansches (5) eine Bohrung (17) aufweist, deren Durchmesser im Wesentlichen gleich dem Durchmesser des Stegs (13) ist.
  2. Scheibe nach Anspruch 1, dadurch gekennzeichnet, dass der radial innere Abschnitt des Reifs (8) in einer hinter dem Steg (13) ausgebildeten Nut (12) aufgenommen ist.
  3. Scheibe nach Anspruch 2, dadurch gekennzeichnet, dass die Nut (12) einen U-förmigen Querschnitt aufweist.
  4. Scheibe nach einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, dass der Durchmesser der Schulter (14), die durch die Nut (12) und die Wand (10) des Hohlraums (7) gebildet ist, einen Durchmesser aufweist, der höchstens gleich dem Durchmesser des Stegs (13) ist.
  5. Scheibe nach Anspruch 4, dadurch gekennzeichnet, dass der Durchmesser der Schulter (14) höchstens gleich dem Durchmesser des Grundes der Kerben (30a) des Stegs (13) ist.
  6. Scheibe nach einem der Ansprüche 2 bis 5, dadurch gekennzeichnet, dass der Reif (8) gegenüberliegende plane Radialflächen aufweist und die Dicke des Reifs (8) höchstens gleich der Breite der Nut (12) ist.
  7. Turbomaschine, dadurch gekennzeichnet, dass sie eine Rotorscheibe nach einem der vorhergehenden Ansprüche umfasst.
EP04291803.7A 2003-07-17 2004-07-15 Rotorscheibe mit einem ringförmigen Flansch Active EP1498579B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308713A FR2857691B1 (fr) 2003-07-17 2003-07-17 Retention de flasque de rotor
FR0308713 2003-07-17

Publications (2)

Publication Number Publication Date
EP1498579A1 EP1498579A1 (de) 2005-01-19
EP1498579B1 true EP1498579B1 (de) 2015-12-02

Family

ID=33462547

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291803.7A Active EP1498579B1 (de) 2003-07-17 2004-07-15 Rotorscheibe mit einem ringförmigen Flansch

Country Status (7)

Country Link
US (1) US7217100B2 (de)
EP (1) EP1498579B1 (de)
JP (1) JP4181528B2 (de)
CA (1) CA2475043C (de)
FR (1) FR2857691B1 (de)
RU (1) RU2340799C2 (de)
UA (1) UA82660C2 (de)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0505186D0 (en) * 2005-03-14 2005-04-20 Cross Mfg 1938 Company Ltd Improvements to a retaining ring
FR2893093B1 (fr) * 2005-11-08 2008-02-08 Snecma Sa Montage d'un anneau composite sur un disque de rotor d'une turbomachine.
FR2899636B1 (fr) * 2006-04-10 2008-07-04 Snecma Sa Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine
EP1956194A1 (de) * 2007-02-06 2008-08-13 Siemens Aktiengesellschaft Turbinenanordnung mit einem Sicherungselement sowie Verfahren zur Sicherung einer Deckplatte
FR2918106B1 (fr) 2007-06-27 2011-05-06 Snecma Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.
EP2182170A1 (de) 2008-10-30 2010-05-05 Siemens Aktiengesellschaft Gasturbine mit Dichtplatten an der Turbinenscheibe
FR2939834B1 (fr) * 2008-12-17 2016-02-19 Turbomeca Roue de turbine avec systeme de retention axiale des aubes
EP2514923A1 (de) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Blendeneinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine
US8643244B2 (en) 2011-07-25 2014-02-04 Hamilton Sundstrand Corporation Strength cast rotor for an induction motor
FR2982635B1 (fr) * 2011-11-15 2013-11-15 Snecma Roue a aubes pour une turbomachine
RU2493371C1 (ru) * 2012-05-11 2013-09-20 Открытое акционерное общество "Авиадвигатель" Ротор турбины турбореактивного двигателя
US9228443B2 (en) * 2012-10-31 2016-01-05 Solar Turbines Incorporated Turbine rotor assembly
WO2014137435A2 (en) * 2013-03-05 2014-09-12 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
US9453422B2 (en) * 2013-03-08 2016-09-27 General Electric Company Device, system and method for preventing leakage in a turbine
FR3009335B1 (fr) * 2013-07-30 2015-09-04 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
FR3020408B1 (fr) * 2014-04-24 2018-04-06 Safran Aircraft Engines Ensemble rotatif pour turbomachine
FR3026430B1 (fr) 2014-09-29 2020-07-10 Safran Aircraft Engines Roue de turbine dans une turbomachine
US10215037B2 (en) * 2016-05-13 2019-02-26 United Technologies Corporation Contoured retaining ring
US10502061B2 (en) 2016-09-28 2019-12-10 Pratt & Whitney Canada Corp. Damper groove with strain derivative amplifying pockets
FR3091719B1 (fr) 2019-01-15 2021-02-12 Safran Aircraft Engines secteur de flasque d’etancheite de disque de rotor
FR3092609B1 (fr) * 2019-02-12 2021-02-12 Safran Aircraft Engines Ensemble de turbine pour turbomachine d’aeronef a circuit de refroidissement de disque ameliore
FR3108669B1 (fr) * 2020-03-25 2022-04-15 Safran Aircraft Engines Roue à aubes d’une turbine d’un aéronef, turbine comportant une telle roue à aubes et procede de montage d’une telle roue à aubes
US11525464B2 (en) 2021-03-23 2022-12-13 Pratt & Whitney Canada Corp. Rotor with centrifugally wedged damper
US11391157B1 (en) 2021-03-23 2022-07-19 Pratt & Whitney Canada Corp. Damped rotor assembly

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
GB2332024B (en) * 1997-12-03 2000-12-13 Rolls Royce Plc Rotary assembly
FR2812906B1 (fr) * 2000-08-10 2002-09-20 Snecma Moteurs Bague de retention axiale d'un flasque sur un disque

Also Published As

Publication number Publication date
CA2475043A1 (fr) 2005-01-17
CA2475043C (fr) 2011-09-27
UA82660C2 (uk) 2008-05-12
US20050042108A1 (en) 2005-02-24
US7217100B2 (en) 2007-05-15
JP2005036811A (ja) 2005-02-10
RU2340799C2 (ru) 2008-12-10
FR2857691A1 (fr) 2005-01-21
RU2004122000A (ru) 2006-01-27
FR2857691B1 (fr) 2006-02-03
JP4181528B2 (ja) 2008-11-19
EP1498579A1 (de) 2005-01-19

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