EP2531700B1 - Gebläse für einen turbinenmotor - Google Patents

Gebläse für einen turbinenmotor Download PDF

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Publication number
EP2531700B1
EP2531700B1 EP11705644.0A EP11705644A EP2531700B1 EP 2531700 B1 EP2531700 B1 EP 2531700B1 EP 11705644 A EP11705644 A EP 11705644A EP 2531700 B1 EP2531700 B1 EP 2531700B1
Authority
EP
European Patent Office
Prior art keywords
radial
disc
lug
flanks
clip
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
EP11705644.0A
Other languages
English (en)
French (fr)
Other versions
EP2531700A1 (de
Inventor
Michaël DELAPIERRE
Patrick Jean-Louis Reghezza
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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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2531700A1 publication Critical patent/EP2531700A1/de
Application granted granted Critical
Publication of EP2531700B1 publication Critical patent/EP2531700B1/de
Active legal-status Critical Current
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
    • 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
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel

Definitions

  • the riders can be engaged axially from upstream on the ears.
  • each rider includes a transverse wall applied on a radial upstream face of an ear and having an orifice aligned with a corresponding orifice of the ear for the passage of a screw or a bolt for fixing on the compressor rotor downstream.
  • each jumper is clamped on a radial ear of a disc at the attachment with the compressor rotor downstream.
  • the thickness of the transverse wall is sufficiently small not to require the replacement of the screw or bolt by fixing screws or bolts of larger dimensions.
  • each transverse wall of the rider comprises at least one radial tab whose free end extends upstream along a rib of the disc.
  • each jumper comprises two aforementioned radial tabs which are parallel and spaced apart circumferentially from one another, which avoids a rotation of the rider during its tightening on the ear.
  • the invention also relates to a jumper for protecting the flanks of a radial lug of a peripheral rib of a fan disk as described above, characterized in that it comprises two substantially parallel lateral lugs connected by a transverse wall comprising a central orifice, the transverse wall of each rider being extended by two bent legs whose free end extends in a direction opposite to the lateral flaps of the rider.
  • Each radial lug 26 comprises lateral flanks comprising each a longitudinal stop 30 projecting.
  • Each abutment 30 formed on the side of an ear 26 is circumferentially aligned with a stop 30 of an adjacent ear ( figure 2 ).
  • jumpers 32 are mounted on the radial lugs 26 of the fan disk 10 and provide a covering of the flanks of the lugs 26 for the protection of the stops 30 ( figure 3 ).
  • the lateral tabs 36, 38 of a jumper 32 each comprise a longitudinal fold 41 in U intended to fit on a longitudinal stop 30 of an ear 26 of the disc 10.
  • This type of ear flange protection jumper 32 can be used both on a new blower disc 10 and on a disc in use. In the latter case, if the stops 30 have a wear, it is necessary to carry out a bleaching by surface of the abutments 30 so as to have a smooth surface in contact with the rider 32. This operation is therefore to remove between 0.2 and 0.5 millimeter of material to the flanks of a worn ear.
  • jumpers 32 on the ears 26 of a fan disk 10 can be achieved when the turbomachine is in place under the wing of the aircraft, which reduces downtime and does not require complicated equipment since each jumper 32 is secured with a pre-existing fastener.
  • the jumpers 32 may be made of a metallic material such as INCONEL and the blades 16 may be made of titanium. In this way the riders 32 wear out less quickly than the blades 16.
  • the jumpers 32 may be made by successive folding and cutting operations of a sheet or by machining a block of material.

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 (7)

  1. Fan eines Turbotriebwerks mit einer Rotorscheibe (10), die an ihrem Außenumfang Ausnehmungen (14) zum Anbringen von Schaufelfüßen (24) aufweist, die von Längsrippen (12) begrenzt werden, enthaltend jeweils einen radial verlaufenden Lappen (26) zur Befestigung der Scheibe (10) an einen stromabwärtigen Verdichterrotor, wobei die Flanken der Lappen (26) Anschläge zum Halten der Schaufeln (16) bilden, die an die Scheibe (10) montiert sind, dadurch gekennzeichnet, dass U-förmige Klemmen (26) an die Lappen der Scheibe montiert sind und jeweils zwei seitliche Laschen (36, 38) aufweisen, welche die Flanken eines radial verlaufenden Lappens überdecken.
  2. Fan nach Anspruch 1, dadurch gekennzeichnet, dass die Klemmen (32) axial von stromaufwärts an die Lappen (26) angreifen.
  3. Fan nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass jede Klemme (32) eine quer verlaufende Wand (34) aufweist, die an einer stromaufwärtigen, radialen Seite eines Lappens (26) anliegt und eine Öffnung (40) aufweist, die für den Durchtritt einer Schraube oder eines Befestigungsbolzens am stromabwärtigen Verdichterrotor mit einer entsprechenden Öffnung (28) des Lappens (32) fluchtet.
  4. Fan nach Anspruch 3, dadurch gekennzeichnet, dass jede seitliche Lasche (36, 38) eine Längskröpfung (41) aufweist, die an einen Anschlag (30) einer Flanke des radial verlaufenden Lappens (26) aufgesteckt ist.
  5. Fan nach Anspruch 3 oder 4, dadurch gekennzeichnet, dass die quer verlaufende Wand (34) der Klemme (32) zumindest eine radial verlaufende Lasche (42, 44) aufweist, deren Ende sich entlang einer Rippe (12) der Scheibe (10) stromaufwärts erstreckt.
  6. Fan nach Anspruch 5, dadurch gekennzeichnet, dass jede Klemme zwei vorgenannte, radial verlaufende Laschen (42, 44) aufweist, die sich parallel erstrecken und umfänglich voneinander beabstandet sind.
  7. Klemme (32), die zum Schutz der Flanken eines radial verlaufenden Lappens (26) einer Umfangsrippe (12) einer Scheibe (10) eines Fans nach einem der Ansprüche 1 bis 6 bestimmt ist, dadurch gekennzeichnet, dass sie zwei seitliche Laschen (36, 38) aufweist, die im wesentlichen parallel verlaufenden und über eine quer verlaufende Wand (34) verbunden sind, die eine mittlere Öffnung (40) aufweist und von zwei umgebogenen Laschen (42, 44) fortgesetzt wird, von denen das freie Ende sich in einer den seitlichen Laschen (36, 38) der Klemme (32) entgegengesetzten Richtung erstreckt.
EP11705644.0A 2010-02-04 2011-01-21 Gebläse für einen turbinenmotor Active EP2531700B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1000456A FR2955904B1 (fr) 2010-02-04 2010-02-04 Soufflante de turbomachine
PCT/FR2011/050116 WO2011095722A1 (fr) 2010-02-04 2011-01-21 Soufflante de turbomachine

Publications (2)

Publication Number Publication Date
EP2531700A1 EP2531700A1 (de) 2012-12-12
EP2531700B1 true EP2531700B1 (de) 2013-12-25

Family

ID=42733744

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11705644.0A Active EP2531700B1 (de) 2010-02-04 2011-01-21 Gebläse für einen turbinenmotor

Country Status (9)

Country Link
US (1) US9376925B2 (de)
EP (1) EP2531700B1 (de)
JP (1) JP5674818B2 (de)
CN (1) CN102753788B (de)
BR (1) BR112012018267B1 (de)
CA (1) CA2786988C (de)
FR (1) FR2955904B1 (de)
RU (1) RU2555099C2 (de)
WO (1) WO2011095722A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3066780B1 (fr) * 2017-05-24 2019-07-19 Safran Aircraft Engines Piece amovible anti-usure pour talon d'aube

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2303148A (en) * 1941-03-24 1942-11-24 Tinnerman Products Inc Nut fastened installations
BE499742A (de) * 1949-03-07
US2727552A (en) * 1953-03-12 1955-12-20 Tinnerman Products Inc Sheet metal retainer for threaded fasteners
US3238495A (en) * 1964-04-17 1966-03-01 Illinois Tool Works Electrical connector
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
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
SU1078981A1 (ru) * 1982-09-17 2005-12-10 С.С. Гасилин Рабочее колесо осевой турбомашины (его варианты)
US4887949A (en) * 1988-03-30 1989-12-19 United Technologies Corporation Bolt retention apparatus
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
JPH07247804A (ja) 1993-01-07 1995-09-26 General Electric Co <Ge> ガスタービンエンジン用のロータ及び動翼アセンブリ、並びに多層被覆シム
US5388963A (en) * 1993-07-02 1995-02-14 United Technologies Corporation Flange for high speed rotors
US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
FR2831207B1 (fr) 2001-10-24 2004-06-04 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif
RU2264561C1 (ru) * 2004-06-08 2005-11-20 Аверичкин Павел Алексеевич Ступень осевого компрессора газотурбинного двигателя
FR2890104A1 (fr) * 2005-08-31 2007-03-02 Snecma Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et moteur d'aeronef les comportant
FR2890105A1 (fr) * 2005-08-31 2007-03-02 Snecma Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes et rotor et motor d'aeronef les comportant
FR2890684B1 (fr) * 2005-09-15 2007-12-07 Snecma Clinquant pour aube de turboreacteur
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
FR2903154B1 (fr) * 2006-06-29 2011-10-28 Snecma Rotor de turbomachine et turbomachine comportant un tel rotor
FR2911632B1 (fr) * 2007-01-18 2009-08-21 Snecma Sa Disque de rotor de soufflante de turbomachine
FR2913735B1 (fr) 2007-03-16 2013-04-19 Snecma Disque de rotor d'une turbomachine
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
FR2939836B1 (fr) 2008-12-12 2015-05-15 Snecma Joint d'etancheite de plateforme dans un rotor de turbomachine

Also Published As

Publication number Publication date
BR112012018267A2 (pt) 2017-06-27
CA2786988A1 (fr) 2011-08-11
BR112012018267B1 (pt) 2020-10-13
FR2955904A1 (fr) 2011-08-05
JP5674818B2 (ja) 2015-02-25
JP2013519030A (ja) 2013-05-23
CN102753788A (zh) 2012-10-24
WO2011095722A1 (fr) 2011-08-11
EP2531700A1 (de) 2012-12-12
CA2786988C (fr) 2017-11-14
RU2012137508A (ru) 2014-03-10
US9376925B2 (en) 2016-06-28
RU2555099C2 (ru) 2015-07-10
FR2955904B1 (fr) 2012-07-20
CN102753788B (zh) 2015-02-11
US20120294721A1 (en) 2012-11-22

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