EP0165860B1 - Axiale Schaufelverriegelung für eine Turbomaschine - Google Patents

Axiale Schaufelverriegelung für eine Turbomaschine Download PDF

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Publication number
EP0165860B1
EP0165860B1 EP85401152A EP85401152A EP0165860B1 EP 0165860 B1 EP0165860 B1 EP 0165860B1 EP 85401152 A EP85401152 A EP 85401152A EP 85401152 A EP85401152 A EP 85401152A EP 0165860 B1 EP0165860 B1 EP 0165860B1
Authority
EP
European Patent Office
Prior art keywords
disc
blade
locking ring
axial
blade root
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.)
Expired
Application number
EP85401152A
Other languages
English (en)
French (fr)
Other versions
EP0165860A1 (de
Inventor
Jean Marc Surdi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0165860A1 publication Critical patent/EP0165860A1/de
Application granted granted Critical
Publication of EP0165860B1 publication Critical patent/EP0165860B1/de
Expired legal-status Critical Current

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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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor

Definitions

  • the present invention relates to an axial locking device for a turbomachine blade.
  • Document FR-A-2 345 605 constitutes the state of the art closest to the invention and has served as a basis for establishing the preamble of the main claim of the present invention.
  • the object of the present invention is to remedy these drawbacks by using a device allowing unitary disassembly of the blades.
  • a locking ring having regularly spaced notches in each of which is inserted an axial protuberance of each blade root projecting downstream of the disc and said axial protuberance of the blade root has on its sides two radial grooves which cooperate with the edges of the notches of the locking ring by lifting the blade foot under the action of the wedge.
  • This locking device makes it possible, compared to French patent 2,507,679, to use a simplified disc and to avoid the presence of teeth both on the blades and on the disc, the realization of which is difficult.
  • the device according to the invention allows unitary disassembly of the blades unlike known collective locks which require unlocking of an entire sector to disassemble a blade.
  • the locking ring according to the invention which is in one piece does not add any additional force to the disc supporting it unlike sectored rings whose centrifugal forces are taken up by the disc.
  • the embodiment in which the locking ring is integrated into the compressor drum has the advantage of a further reduction in the number of parts because the attachment of the disc to the drum is achieved by means of the ring of locking.
  • Figure 1 there is shown a disc 1 of a turbomachine rotor having at the upper part of the upstream face a rim which is smooth, the lower part of the rim having a flange 2 on which is fixed a conical front cover 3 .
  • the rim of the disc 1 On its downstream face the rim of the disc 1 has a radial flange 5 which is intended for fixing, by bolts 6 of a locking ring 7 and of a sealing ring 8.
  • the sealing ring 8 comes to bear on the downstream edge of the platform 9 of the vanes 10 and its internal edge on the drum 11 of the intermediate compressor.
  • a lower flange 12 is also provided on the downstream face of the rim of the disc 1 and on this flange is fixed the drum 11 of the low pressure compressor.
  • Each blade 10 is mounted on the disk 1 by means of a foot 13 with a section in the shape of a dovetail and which is slidably engaged in a cell 4 of the disk, said blade foot 13 being locked radially by a wedge 14 engaged between said foot 13 of the blade and the bottom of the cell 4.
  • the wedge 14 bears on one side against a stop 15 of the front cover 3 and on the other side against a flange 16 of the drum 11.
  • the rear part of the blade root 13 is extended by an axial protuberance 17 which is engaged in one of the notches 18 ( Figures 1, 3, 4 and 5) provided in the locking ring 7, said notches are regularly spaced in number equal to that of the blades.
  • the notches 18 of the ring 7 are located opposite the cells 4 of the disc rim and their sides partially mask each side of the cells 4.
  • the axial protuberance 17 which projects beyond the downstream face of the disc has two radial grooves 19, 19a machined on the sides of said protuberance ( Figures 3 and 5).
  • the grooves 19, 19a are engaged on the edges of the notch 18 of the locking ring 7 during the lifting of the foot 13 of the blade under the action of the wedge 14 thus ensuring the axial locking of the blade 10 .
  • the rear part of the foot 13 is extended by a radial protuberance 20 which can come to bear against the bottom of the notch 18, in the case of loss of a blade.
  • Each blade 10 is inserted from front to back into the corresponding socket 4 of the disc, until the rear face of the stilt comes to bear on the ring.
  • the front cover 3 is mounted on the flange 2 which axially locks the shims 4 in abutment against the flange 15.
  • the cover 3 is removed and the shim 14 is deposited, which has the effect of allowing the blade to descend to the bottom of the cell 4 and to release the rear part and the protuberance 17 of the locking ring 7.
  • the locking ring 7 is integrated into the drum 22 of the low pressure compressor and forms only one piece with it.
  • the ring 7 has, as previously, indentations 18 in which is engaged by radial grooves 19, 19a the protuberance 17 of the foot 13 of the dawn.

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)

Claims (3)

1. Vorrichtung zur axielen Verriegelung einer Turbomaschinen-Schaufel,
bei der der Krenz der Rotorscheibe im wesentlichen axial angeordnete Zellen mit schwelbenschwanzförmigem Querschnitt aufweist, die die entsprechend geformten Scheufelfüße aufnehmen, welche in radialer Richtung durch zwischen, dem Schaufelfuß und dem Boden der Zelle angeordnete Keile verriegelt sind,
und bei der auf der stromabwärtigen Seite der Rotorscheibe (1) ein Verriegelungsring (7) befestigt ist,
dadurch gekennzeichnet,
daß der Verriegelungsring in regelmäßigen Abständen angeordnete Ausnehmungen (18) aufweist, in denen jeweils ein axialer Vorsprung (17) des betreffenden Schaufelfußes (13) eingesetzt ist, der in stromabwärtiger Richtung von der Rotorscheibe (1) wegragt,
und daß dieser axiale Vorsprung (17) des Schaufelfußes (13) an seinen Flanken zwei radiale Einschnitte (19, 19a) aufweist, die mit den Rändern, der Ausnehmungen (18) des Verriegelungsrings (7) zusammenwirken, wenn der Schaufelfuß (13) durch die Wirkung des Keils (14) angehoben wird.
2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der Verriagelungsring (7) mit Hilfe von Schraubbolzen (6) zwischen der Rotorscheibe (1) und einem Dichtungsring (8) eingespannt ist, wobei dieser Dichtungsring (8) mit seinem Außanrand an dem stromabwärtigen Rand der Plattformen (9) der Schaufeln (10) und mit seinem Innenrand an der Trommel (11) des Niederdruckverdichters anliegt.
3. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der mit Ausnehmungen (18) versehene Verriegelungsring (7) integraler Bestandteil der Trommel (22) des Niederdruckverdichters ist.
EP85401152A 1984-06-14 1985-06-12 Axiale Schaufelverriegelung für eine Turbomaschine Expired EP0165860B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8409286A FR2566061B1 (fr) 1984-06-14 1984-06-14 Dispositif de verrouillage axial d'une aube de turbomachine
FR8409286 1984-06-14

Publications (2)

Publication Number Publication Date
EP0165860A1 EP0165860A1 (de) 1985-12-27
EP0165860B1 true EP0165860B1 (de) 1988-03-16

Family

ID=9304994

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85401152A Expired EP0165860B1 (de) 1984-06-14 1985-06-12 Axiale Schaufelverriegelung für eine Turbomaschine

Country Status (5)

Country Link
US (1) US4604033A (de)
EP (1) EP0165860B1 (de)
JP (1) JPS6111404A (de)
DE (1) DE3561897D1 (de)
FR (1) FR2566061B1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2585069B1 (fr) * 1985-07-16 1989-06-09 Snecma Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
FR2681374B1 (fr) * 1991-09-18 1993-11-19 Snecma Fixation d'aube de souflante de turboreacteur.
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
FR2841933B1 (fr) * 2002-07-04 2004-12-03 Snecma Moteurs Cale autobloquante
JP4911286B2 (ja) * 2006-03-14 2012-04-04 株式会社Ｉｈｉ ファンのダブテール構造
JP4807113B2 (ja) * 2006-03-14 2011-11-02 株式会社Ｉｈｉ ファンのダブテール構造
US20090053064A1 (en) * 2006-09-01 2009-02-26 Ress Jr Robert A Fan blade retention system
FR2915495B1 (fr) 2007-04-30 2010-09-03 Snecma Procede de reparation d'une aube mobile de turbomachine
US9662721B2 (en) * 2008-02-26 2017-05-30 United Technologies Corporation Method of generating a curved blade retention slot in a turbine disk
FR2929660B1 (fr) 2008-04-07 2012-11-16 Snecma Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure
US8419370B2 (en) * 2009-06-25 2013-04-16 Rolls-Royce Corporation Retaining and sealing ring assembly
FR2948725B1 (fr) * 2009-07-28 2012-10-05 Snecma Dispositif anti-usure d'un rotor de turbomachine
FR2965843B1 (fr) * 2010-10-06 2012-11-09 Snecma Rotor pour turbomachine
FR2972759B1 (fr) * 2011-03-15 2015-09-18 Snecma Systeme d'etancheite et de retenue axiale des aubes pour une roue de turbine de turbomachine
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
FR2986284B1 (fr) 2012-01-31 2014-03-28 Snecma Procede de reparation de marques d’usure.
FR3075284B1 (fr) * 2017-12-18 2020-09-04 Safran Aircraft Engines Dispositif amortisseur

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
FR2492906A2 (fr) * 1976-03-25 1982-04-30 Snecma Dispositif de retenue pour aubes de soufflantes
FR2345605A1 (fr) * 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
FR2507679A1 (fr) * 1981-06-12 1982-12-17 Snecma Dispositif de verrouillage d'une aube de rotor de turbomachine
US4453890A (en) * 1981-06-18 1984-06-12 General Electric Company Blading system for a gas turbine engine
FR2519072B1 (fr) * 1981-12-29 1986-05-30 Snecma Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur
US4451205A (en) * 1982-02-22 1984-05-29 United Technologies Corporation Rotor blade assembly
FR2524932A1 (fr) * 1982-04-08 1983-10-14 Snecma Dispositif de retenue axiale de pieds d'aube dans un disque de turbomachine
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
FR2535793B1 (fr) * 1982-11-08 1987-04-10 Snecma Dispositif de verrouillage axial d'aubes de soufflante

Also Published As

Publication number Publication date
DE3561897D1 (en) 1988-04-21
JPS6111404A (ja) 1986-01-18
FR2566061A1 (fr) 1985-12-20
FR2566061B1 (fr) 1988-09-02
US4604033A (en) 1986-08-05
EP0165860A1 (de) 1985-12-27
JPH0340204B2 (de) 1991-06-18

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