EP0113598B1 - Dispositif de verrouillage axial d'aubes de soufflante - Google Patents

Dispositif de verrouillage axial d'aubes de soufflante Download PDF

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Publication number
EP0113598B1
EP0113598B1 EP83402058A EP83402058A EP0113598B1 EP 0113598 B1 EP0113598 B1 EP 0113598B1 EP 83402058 A EP83402058 A EP 83402058A EP 83402058 A EP83402058 A EP 83402058A EP 0113598 B1 EP0113598 B1 EP 0113598B1
Authority
EP
European Patent Office
Prior art keywords
disc
tongue
blade
root
axial
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
EP83402058A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0113598A1 (fr
Inventor
Georges Kebedjis
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 EP0113598A1 publication Critical patent/EP0113598A1/fr
Application granted granted 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
    • 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
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/22—Three-dimensional parallelepipedal

Definitions

  • the present invention relates to a turbomachine fan wheel comprising means for axially locking the blades.
  • U.S. Patent 4,033,705 relates to a device in which the rotor disk has teeth at its periphery having radial grooves arranged one opposite the other and in which a shaped locking member is engaged dovetail against which abuts by an elastic element the foot of the blade, said locking member having tabs which are in abutment against an annular ring fixed on the upstream face of the disc.
  • the retaining plate is housed in a circumferential groove closed in the direction of the center and not in radial slots open in the direction of the center.
  • the retaining plate requires for its maintenance a second circumferential groove provided in a flange of the upstream face of the disc.
  • the introduction or removal of the retaining plate in the grooves is effected by deformation, which prohibits the use of a thick plate and having a resistance comparable to that which is desired according to the invention.
  • French patents 2013647 and 2345605 relate to a device in which the blade root carries a nose which is provided with radial slots corresponding to the grooves of the teeth and in which a U-shaped locking member is engaged.
  • EP-A-0061 948 has also proposed a device in which a key placed at the end of the blade root engages in grooves made in the disc. In view of its radial immobilization the key carries a threaded rod which is used for fixing the front cover of the blower. Unfortunately, this device does not allow disassembly and reassembly separate from each blade.
  • the object of the present invention is to remedy these drawbacks and to obtain a simple device allowing the separate disassembly and reassembly of each of the blades.
  • a turbomachine fan wheel comprising means for axially locking the blades allowing the disassembly and unitary reassembly thereof, each blade comprising a dovetail foot capable of being engaged by axial sliding in corresponding cells of the rim of the disc, said foot carrying a heel abutting against the upstream face of the disc, the rim of the disc having at its periphery teeth projecting towards the front having radial grooves arranged facing one on the other and in which is housed an axial locking member of the blade root, is characterized in that the locking member consists of a parallelepipedal shaped key against which the foot of the blade, and in that two adjacent keys are locked radially inwardly by a cleat whose middle branch is fixed against the upstream face of the tooth and whose transverse branches s bear under a wing of each of the two adjacent keys extending in the axial direction the large upstream face of said key.
  • the parallelepipedal part of the key has, at at least one of its circumferential ends, a bore perpendicular to the face of the tooth in which it is engaged, said tooth comprising it even a bore corresponding to the bore of the key for the introduction into these bores of a means for fixing the key thus ensuring the radial locking of the key inwards.
  • This arrangement makes it possible to obtain a simpler locking device than those existing, in particular as regards the holding of the key in the centrifugal direction.
  • FIG. 1 there is shown a disc 1 of a fan rotor having a rim in which are formed cells 2 having in section the shape of a dovetail.
  • cells 2 having in section the shape of a dovetail.
  • the foot 3 carries a heel 5 which comes abut against the upstream face of the disc 1 and prevents the axial movement of the blade from upstream to downstream.
  • the rim of the disc 1 has at its periphery teeth 6, 6a disposed on either side of each cell 2 and projecting axially towards the front, said teeth being provided with radial grooves 7, 7a arranged opposite one another and in which is housed an axial locking member of the foot 3 of the blade.
  • the locking member consists of a rectangular parallelepipedal key 8 against which the foot 3 of the blade comes into abutment.
  • the key 8 is locked radially inwards by a cleat 9, a middle branch 9a of which is fixed by means of a screw 10 against the upstream face of the tooth 6, 6a and of which a transverse branch 9b perpendicular to the branch 9a is resting under a wing 8a of the key extending in the axial direction the large upstream face of said key.
  • the wing 8a of the key and the branch 9b of the cleat 9 have a thinned part 8b on the wing 8a and 9c on the branch 9b, in order to allow the superposition of the wing and the branch.
  • the cleat 9 thus ensures the radial retention of two keys 8 adjacent to each tooth, such as 6a.
  • the axial locking member of the foot 3 of the blade 4 consists of a rectangular parallelepipedal key 12 which is engaged, at its ends, in the two radial grooves 7, 7a of the teeth 6, 6a, the foot 3 of the blade coming to bear against the central part of the key 12.
  • the key 12 is locked radially at at least one of its circumferential ends by a stud screw 13 engaged in corresponding bores 14 and 15 provided in the tooth 6a and in the key 12.
  • the bore 15 of the key is perpendicular to the face of the tooth 6a in which said key is engaged.
  • the stud screw 13 is screwed into a tapped hole in the upstream face of the disc.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP83402058A 1982-11-08 1983-10-24 Dispositif de verrouillage axial d'aubes de soufflante Expired EP0113598B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8218652A FR2535793B1 (fr) 1982-11-08 1982-11-08 Dispositif de verrouillage axial d'aubes de soufflante
FR8218652 1982-11-08

Publications (2)

Publication Number Publication Date
EP0113598A1 EP0113598A1 (fr) 1984-07-18
EP0113598B1 true EP0113598B1 (fr) 1987-04-22

Family

ID=9278973

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83402058A Expired EP0113598B1 (fr) 1982-11-08 1983-10-24 Dispositif de verrouillage axial d'aubes de soufflante

Country Status (5)

Country Link
US (1) US4502841A (enrdf_load_stackoverflow)
EP (1) EP0113598B1 (enrdf_load_stackoverflow)
JP (1) JPS59101598A (enrdf_load_stackoverflow)
DE (1) DE3371106D1 (enrdf_load_stackoverflow)
FR (1) FR2535793B1 (enrdf_load_stackoverflow)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2566061B1 (fr) * 1984-06-14 1988-09-02 Snecma Dispositif de verrouillage axial d'une aube de turbomachine
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
US5486095A (en) * 1994-12-08 1996-01-23 General Electric Company Split disk blade support
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
US8016561B2 (en) 2006-07-11 2011-09-13 General Electric Company Gas turbine engine fan assembly and method for assembling to same
FR2905139B1 (fr) * 2006-08-25 2012-09-28 Snecma Aube de rotor d'une turbomachine
EP1916389A1 (en) * 2006-10-26 2008-04-30 Siemens Aktiengesellschaft Turbine blade assembly
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
FR2930595B1 (fr) * 2008-04-24 2011-10-14 Snecma Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
FR2945329B1 (fr) * 2009-05-06 2011-06-03 Snecma Rotor de soufflante d'un turboracteur d'avion
US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component
JP5561461B2 (ja) * 2009-06-09 2014-07-30 株式会社Ｉｈｉ 動翼保持構造
US10352209B2 (en) 2015-11-25 2019-07-16 Solberg Mfg., Inc. Pressure regulator assemblies
US10371163B2 (en) * 2016-02-02 2019-08-06 General Electric Company Load absorption systems and methods
FR3057908B1 (fr) * 2016-10-21 2019-11-22 Safran Aircraft Engines Ensemble rotatif d'une turbomachine muni d'un systeme de maintien axial d'une aube
KR101919228B1 (ko) * 2017-03-16 2018-11-15 두산중공업 주식회사 버킷의 축 방향 고정 장치와 버킷 조립체 및 이를 포함하는 가스터빈
IT201900014724A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
FR3139360B1 (fr) * 2022-09-02 2024-07-26 Safran Aircraft Engines Roue mobile pour turbomachine comprenant des aubes bloquées axialement
FR3139596B1 (fr) * 2022-09-12 2024-07-26 Safran Aircraft Engines Ensemble de turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB739870A (en) * 1954-04-07 1955-11-02 Parsons C A & Co Ltd Improvements in and relating to locking devices for rotor blades of turbines and the like
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
BE794573A (fr) * 1972-02-02 1973-05-16 Gen Electric Dispositif de fixation d'aubes
SU445753A1 (ru) * 1972-03-27 1974-10-05 Предприятие П/Я Р-6197 Устройство дл фиксации рабочих лопаток
FR2345605A1 (fr) * 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur

Also Published As

Publication number Publication date
DE3371106D1 (en) 1987-05-27
FR2535793A1 (fr) 1984-05-11
JPS59101598A (ja) 1984-06-12
US4502841A (en) 1985-03-05
EP0113598A1 (fr) 1984-07-18
FR2535793B1 (fr) 1987-04-10
JPS6367040B2 (enrdf_load_stackoverflow) 1988-12-22

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