EP0110744A1 - Radial- und Axialbefestigung einer Verdichterschaufel - Google Patents

Radial- und Axialbefestigung einer Verdichterschaufel Download PDF

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Publication number
EP0110744A1
EP0110744A1 EP83402057A EP83402057A EP0110744A1 EP 0110744 A1 EP0110744 A1 EP 0110744A1 EP 83402057 A EP83402057 A EP 83402057A EP 83402057 A EP83402057 A EP 83402057A EP 0110744 A1 EP0110744 A1 EP 0110744A1
Authority
EP
European Patent Office
Prior art keywords
wedge
blade
foot
sheath
engaged
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
EP83402057A
Other languages
English (en)
French (fr)
Other versions
EP0110744B1 (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
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0110744A1 publication Critical patent/EP0110744A1/de
Application granted granted Critical
Publication of EP0110744B1 publication Critical patent/EP0110744B1/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 and radial retaining device for fan blades.
  • Axial and radial blade retaining devices are known, such as that described in French patent 2,345,605, which consists of a shim which is placed between the foot of the blade and the bottom of a groove or recess provided in the rim of the rotor disc so as to press the part of the blade root dovetail radially furthest from the axis against the lateral teeth of the groove, the wedge being held in the axial direction by a U-shaped lock which cooperates with corresponding notches provided in the root of the blade and in the teeth of the groove.
  • This device also includes a corner interposed between the beak of the wedge and the front of the blade root.
  • the centrifugal force exerted on the blades is no longer sufficient to keep the blade roots pressed at the same time on the two oblique faces of the grooves.
  • the blades pass from a support position on one side of the cell to a support position on the other side. This produces a rattling and, what is more serious, a mat which very seriously damages the surfaces in contact. If such damage is already difficult to accept for easily replaceable parts, such as shims or, if need be, the blades, it is not the same for the rotor disc for which such damage is absolutely unacceptable.
  • French patent 2,029,000 relates to a device for radial attachment of a fan blade comprising a shim made of molded elastomer material interposed between the root of the blade and the bottom of the groove or cell.
  • This elastomer spacer plays a role of damping and reduction of the friction zones between the foot of the blade and the cell; however, this device does not include a metallic element under stress exerting a significant force against the blade root.
  • French patent 2,376,958 is also known, which relates to a vibration damping device consisting of an element made of elastomer material in which an elastically deformable metal part is embedded.
  • the thin steel sheet molded in the elastomer does not really exert a force in the radial direction on the blades, but acts only to keep the damper in contact with the plates.
  • the present invention relates to a device for exerting on the foot of the blade a significant effort in the radial direction and to improve the resistance of the coatings applied to the bulb of the blade root or on the sides of the disc alveoli.
  • an axial and radial fan blade retention device in which the blade comprises a dovetail foot capable of being engaged by axial sliding in corresponding cells of the rim of the rotor disc, the rim of the disc having, at its periphery, teeth projecting axially towards the front, provided with radial grooves arranged opposite one another and in which is housed an axial locking means of the blade root, the device comprising an elastic shim interposed between the blade root and the bottom of the groove to exert on the foot of the blade a force directed radially outwards and a wedge for preloading the wedge, interposed between the wedge and the lower front face of the blade foot, characterized in that it comprises a sheath made of elastomeric material in the form of a gutter extending axially and interposed between the wedge, the sides and the bottom of the cell, said sheath having an opening in which is engaged a stop of the wedge constituting a central bearing of the wedge on the bottom of the cell.
  • the sheath ensures the centering of the shim in the cell and it also performs the function of axial stop. Furthermore, this elastomer sheath is interposed between the sides of the cell and the wedge and it reduces the surface of the areas in contact.
  • the shims can be cut from a stretched or machined profile, so that this results in simplified and less costly manufacture.
  • FIGS 1 and 2 there is shown a disc 1 of a fan rotor having a rim in which are formed axially oriented cells or grooves 2 having in section the shape of a dovetail.
  • each of the cells 2 is engaged by axial sliding a foot 3 of a blade 4 which comprises a blade 5, a platform 6 and a stilt 7 connecting the blade to the foot 3.
  • the foot 3 has a tail-shaped section dovetail corresponding to that of groove 2.
  • the rim of the disc 1 has at its periphery teeth 8, 8a projecting axially forwardly provided with radial grooves 9, 9a arranged opposite one another and in which is housed a member 10 for axial locking of the foot 3 of dawn.
  • the locking member 10 consists of a rectangular parallelepiped whose lateral edges 11, lla rounded are engaged in the radial grooves 9, 9a and which has on its outer edge a tongue 12 abutting under the upstream edge of the plate -form 6 of dawn ( Figure 2).
  • a stop 14 located in its central part is engaged in an opening or cut 15 of a sheath 16 of elastomer material in the form of gutter extending axially and interposed between the wedge 13, the sides and the bottom of the cell 2.
  • the central stop 14 which bears against the bottom of the cell 2 constitutes a central bearing of the wedge 13 on the bottom of the cell and ensures by its engagement in the opening 15 of the sheath the axial maintenance of the wedge.
  • the wedge 13 further comprises a safety stop 20, also engaged in an opening 21 of the sheath.
  • the elastic wedge 13 has at the front a spout 17 comprising a hole 18 to facilitate its extraction by means of a tool; at the rear, the wedge has a stop 19 which bears against the foot 3 of the blade.
  • the sheath 16 engaged in the cell 2 has at the front a spoiler 22 bearing against the front face of the disc 1.
  • a wedge 23 which maintains the preload of the wedge 13, said wedge being held by a front cover 24 fixed by means of screws 25 to the disc 1.
  • the foot 3 of the blade is slid into the cell 2 until its upstream face is flush with the upstream face of the disc 1.
  • the blade 4 is locked axially by means of the locking member 10 which is introduced from the inside to the outside into the grooves 9, 9a of the disc.
  • the locking member 10 abuts by its tongue 12 against the internal face of the platform 6, and it is held in this position by means of a clamp.
  • the wedge 13 is inserted into the sheath 16, the stop 14 being engaged in the opening 15 of the sheath.
  • the assembly thus constituted by the wedge 13 and the sheath 16 is engaged in the cavity 2 of the disc, under the foot 3 of the blade, until the spoiler 22 abuts against the front face of the disc 1 You can then remove the clamp holding the locking member.
  • the elastic wedge 13 is curved towards the axis of the machine. After the introduction of the wedge 23 between the wedge and the foot of the blade, the wedge is released, so that, by reaction, the elastic wedge 13 presses the foot 3 of the blade against the flanks of the disc.
  • the corner 23 is then locked in place by means of the front cover 24 fixed to the disc.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP83402057A 1982-11-08 1983-10-24 Radial- und Axialbefestigung einer Verdichterschaufel Expired EP0110744B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8218653 1982-11-08
FR8218653A FR2535794A1 (fr) 1982-11-08 1982-11-08 Dispositif de retenue axiale et radiale d'aubes de soufflante

Publications (2)

Publication Number Publication Date
EP0110744A1 true EP0110744A1 (de) 1984-06-13
EP0110744B1 EP0110744B1 (de) 1986-10-01

Family

ID=9278974

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83402057A Expired EP0110744B1 (de) 1982-11-08 1983-10-24 Radial- und Axialbefestigung einer Verdichterschaufel

Country Status (5)

Country Link
US (1) US4478554A (de)
EP (1) EP0110744B1 (de)
JP (1) JPS59101599A (de)
DE (1) DE3366620D1 (de)
FR (1) FR2535794A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262139A (en) * 1991-12-04 1993-06-09 Rolls Royce Plc Fan blade retainer
EP0699824A1 (de) * 1994-08-29 1996-03-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
WO2011018425A1 (fr) * 2009-08-11 2011-02-17 Snecma Cale amortisseuse de vibrations pour aube de soufflante
FR2974864A1 (fr) * 2011-05-04 2012-11-09 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
EP2865849A1 (de) * 2013-10-22 2015-04-29 Rolls-Royce plc Rückhalteplatte
WO2018093473A1 (en) * 2016-11-18 2018-05-24 General Electric Company Turbomachine bucket with radial support, shim and related turbomachine rotor
EP4036374A1 (de) * 2021-02-02 2022-08-03 Doosan Heavy Industries & Construction Co., Ltd. Drehmaschine mit einer rotorscheibe und schaufeln
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly

Families Citing this family (41)

* 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
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
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
JPH04161698A (ja) * 1990-10-26 1992-06-05 K F C:Kk トンネルのコンクリート覆工施工法
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
GB9223593D0 (en) * 1992-11-11 1992-12-23 Rolls Royce Plc Gas turbine engine fan blade assembly
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
FR2728299B1 (fr) * 1994-12-14 1997-01-24 Snecma Dispositif de fixation axiale d'aubes de rotor de turboreacteur
FR2746456B1 (fr) * 1996-03-21 1998-04-30 Snecma Dispositif de retenue du pied des aubes d'une soufflante
ITMI991210A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Dispositivo di fissaggio per palette per turbine a gas
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
US6739837B2 (en) 2002-04-16 2004-05-25 United Technologies Corporation Bladed rotor with a tiered blade to hub interface
GB0216951D0 (en) * 2002-07-20 2002-08-28 Rolls Royce Plc A fan blade assembly
JP2005273646A (ja) * 2004-02-25 2005-10-06 Mitsubishi Heavy Ind Ltd 動翼体及びこの動翼体を有する回転機械
FR2888897B1 (fr) * 2005-07-21 2007-10-19 Snecma Dispositif d'amortissement des vibrations d'un anneau de retention axiale des aubes de soufflante d'une turbomachine
FR2889264B1 (fr) * 2005-07-29 2007-11-02 Snecma Verrouillage des aubes dans un rotor de soufflante
US20080226455A1 (en) * 2007-03-15 2008-09-18 Grimesey Daren T Quick click
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
US8182229B2 (en) * 2008-01-14 2012-05-22 General Electric Company Methods and apparatus to repair a rotor disk for a gas turbine
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
EP2184443A1 (de) 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe
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
US8215915B2 (en) * 2009-05-15 2012-07-10 Siemens Energy, Inc. Blade closing key system for a turbine engine
GB0914969D0 (en) * 2009-08-28 2009-09-30 Rolls Royce Plc An aerofoil blade assembly
GB2474449B (en) * 2009-10-14 2012-02-22 Rolls Royce Plc Annulus filler element for a rotor of a turbomachine
US8876479B2 (en) 2011-03-15 2014-11-04 United Technologies Corporation Damper pin
US8951014B2 (en) * 2011-03-15 2015-02-10 United Technologies Corporation Turbine blade with mate face cooling air flow
DE102013205948B4 (de) * 2013-04-04 2015-03-12 MTU Aero Engines AG Sicherungssystem und Verfahren zur Sicherung eines Befestigungsbereichs wenigstens einer Rotorschaufel oder eines Rotorschaufelsegments in einem Montagebereich eines Rotorgrundkörpers
US9970297B2 (en) 2014-08-29 2018-05-15 Rolls-Royce Corporation Composite fan slider with nano-coating
US10215035B2 (en) * 2014-12-29 2019-02-26 Rolls-Royce North American Technologies Inc. Turbine wheels with preloaded blade attachment
EP3073052B1 (de) * 2015-02-17 2018-01-24 Rolls-Royce Corporation Bläserbaugruppe
GB201503303D0 (en) 2015-02-27 2015-04-15 Rolls Royce Plc Retention device
US10472975B2 (en) * 2015-09-03 2019-11-12 General Electric Company Damper pin having elongated bodies for damping adjacent turbine blades
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
FR3075284B1 (fr) * 2017-12-18 2020-09-04 Safran Aircraft Engines Dispositif amortisseur
CN115751480A (zh) * 2021-09-03 2023-03-07 广东美的暖通设备有限公司 风机组件、空调室外机及空调器
US12410720B2 (en) * 2023-11-02 2025-09-09 General Electric Company Turbine engine having a rotatable disk and a blade

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1570396A (de) * 1967-09-21 1969-06-06
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
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
FR2426151A1 (fr) * 1978-05-18 1979-12-14 Gen Electric Dispositif de blocage des aubes de rotor
GB2026101A (en) * 1978-07-22 1980-01-30 Rolls Royce Rotor blade fixing
GB2038959A (en) * 1979-01-02 1980-07-30 Gen Electric Turbomachinery blade retaining assembly

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
GB1491480A (en) * 1975-07-28 1977-11-09 Rolls Royce Fixing blades for fluid flow machines
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

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1570396A (de) * 1967-09-21 1969-06-06
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
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
FR2426151A1 (fr) * 1978-05-18 1979-12-14 Gen Electric Dispositif de blocage des aubes de rotor
GB2026101A (en) * 1978-07-22 1980-01-30 Rolls Royce Rotor blade fixing
GB2038959A (en) * 1979-01-02 1980-07-30 Gen Electric Turbomachinery blade retaining assembly

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262139A (en) * 1991-12-04 1993-06-09 Rolls Royce Plc Fan blade retainer
EP0699824A1 (de) * 1994-08-29 1996-03-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
DE4430636A1 (de) * 1994-08-29 1996-03-14 Mtu Muenchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorunwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
US8911210B2 (en) 2009-08-11 2014-12-16 Snecma Vibration-damping shim for fan blade
FR2949142A1 (fr) * 2009-08-11 2011-02-18 Snecma Cale amortisseuse de vibrations pour aube de soufflante
WO2011018425A1 (fr) * 2009-08-11 2011-02-17 Snecma Cale amortisseuse de vibrations pour aube de soufflante
FR2974864A1 (fr) * 2011-05-04 2012-11-09 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
EP2865849A1 (de) * 2013-10-22 2015-04-29 Rolls-Royce plc Rückhalteplatte
US9745995B2 (en) 2013-10-22 2017-08-29 Rolls-Royce Plc Retainer plate
WO2018093473A1 (en) * 2016-11-18 2018-05-24 General Electric Company Turbomachine bucket with radial support, shim and related turbomachine rotor
US10400614B2 (en) 2016-11-18 2019-09-03 General Electric Company Turbomachine bucket with radial support, shim and related turbomachine rotor
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
EP4036374A1 (de) * 2021-02-02 2022-08-03 Doosan Heavy Industries & Construction Co., Ltd. Drehmaschine mit einer rotorscheibe und schaufeln
US11702942B2 (en) 2021-02-02 2023-07-18 Doosan Enerbility Co., Ltd. Rotary machine, gas turbine including same, and rotary machine assembly method

Also Published As

Publication number Publication date
JPS6323397B2 (de) 1988-05-16
FR2535794B1 (de) 1985-01-11
FR2535794A1 (fr) 1984-05-11
US4478554A (en) 1984-10-23
JPS59101599A (ja) 1984-06-12
DE3366620D1 (en) 1986-11-06
EP0110744B1 (de) 1986-10-01

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