EP2531700A1 - Soufflante de turbomachine - Google Patents
Soufflante de turbomachineInfo
- Publication number
- EP2531700A1 EP2531700A1 EP11705644A EP11705644A EP2531700A1 EP 2531700 A1 EP2531700 A1 EP 2531700A1 EP 11705644 A EP11705644 A EP 11705644A EP 11705644 A EP11705644 A EP 11705644A EP 2531700 A1 EP2531700 A1 EP 2531700A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- radial
- disc
- flanks
- disk
- rider
- 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
Links
- 210000005069 ears Anatomy 0.000 claims description 19
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 230000008439 repair process Effects 0.000 description 5
- 241000272165 Charadriidae Species 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000005119 centrifugation Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000004061 bleaching Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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 present invention relates to a fan of a turbomachine, such as an airplane turbojet or turboprop.
- a turbomachine fan comprises a rotor disk having on its outer periphery a plurality of longitudinal ribs delimiting between them axial mounting and radial retaining cells of blade roots.
- the downstream end of each rib comprises a radial lug having a hole for the passage of a screw or a bolt for fixing the fan disk to an upstream flange of a low-pressure compressor arranged downstream of the fan.
- the low-pressure compressor is thus rotated with the rotor of the fan by a turbine shaft.
- each ear form retaining stops of the blades and thus limit their angular deflection.
- the dawn disengaged from the disk impacts an adjacent blade which tilts angularly and bears on the side of an ear, which allows a transfer of the energy released by the shock of the dawn disengaged on the adjacent blade towards the entire disk and thus avoids cascading blade losses.
- the rotating parts of the turbomachine can undergo an autorotation (called "windmilling" in English). Indeed, the air entering the interior of the turbomachine induces a rotation of the rotor of the fan at a speed of the order of 40 to 50 revolutions per minute. This low rotational speed does not allow sufficiently large centrifugation of the blades for blocking in position in the cells. As a result, the blades of the blower can tilt over the flanks of the ears of the ribs of the disc. These repeated contacts induce friction between the flanks of the ears and the blades leading to premature wear of the stops, which requires more frequent repairs stops. At present, the repair of the flanks of the ears is performed by plasma deposition of a metal layer. However, the repaired disk ears have less fatigue resistance than the ears of a new disc. In addition, these material deposits have a limited impact resistance and can break down gradually over time.
- the invention aims in particular to provide a simple, economical and effective solution to these various problems.
- a turbomachine blower comprising a rotor disc having on its outer periphery mounting cells of blade roots delimited by longitudinal ribs each having a radial lug for fixing the disk to a compressor rotor. downstream, the flanks of the ears forming retaining stops of the vanes mounted on the disk, characterized in that U-shaped riders are mounted on the ears of the disc and each comprise two lateral lugs covering the flanks of a radial lug.
- the invention thus proposes the integration of protection riders of the ears of the disk avoiding wear of the flanks of the ears by repeated contact of the blades when the blower is put into autorotation.
- 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 fixing bolt 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 lateral leg of a rider comprises a longitudinal U-fold fitting on a stop of a flange of the radial lug, which makes it possible to ensure the axial mounting of the rider on one ear and the radial retention of this rider on that ear.
- 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.
- FIG. 2 is a partial schematic cross sectional view of a blade mounted in a cell of a fan disk according to the prior art
- FIG. 3 is a diagrammatic view from the upstream side of a portion of a disc comprising means for protecting the ears of the disc according to the invention
- FIGS. 4A and 4B are perspective views of protective jumpers for the radial ears of a disc of a blower according to the invention.
- FIG. 5 is a schematic axial sectional view of the attachment of the fan disk according to the invention to a low pressure compressor rotor arranged downstream.
- FIG. 1 shows schematically a part of a turbomachine fan disk 10 comprising at its outer periphery longitudinal ribs 12 delimiting between them of the cells 14 of axial mounting and radial retaining d blades 16.
- Each blade 16 comprises a blade 18, a platform 20 formed at the base of the blade and internally defining the annular flow of the stream of air entering the turbomachine.
- An area 22 called “stilt” connects the platform 20 and the blade 18 at the blade root 24.
- Each rib 12 of the fan disk 10 comprises a radial lug 26 formed at its downstream end.
- These lugs 26 each comprise an axial orifice 28 intended to be aligned with a corresponding orifice formed in an annular flange of a low-pressure compressor rotor arranged downstream (see FIG. 5). Fixing screws are inserted into the orifices 28 of the lugs 26 of the disk 10 and into the orifices of the annular flange of the compressor rotor.
- 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 (FIG. 2).
- jumpers 32 are mounted on the radial ears 26 of the fan disk 10 and provide a covering of the flanks of the ears 26 for the protection of the stops 30 ( Figure 3).
- Each rider has a U-shape and includes a transverse wall
- the transverse wall 34 comprises a central orifice 40 and is extended by two radial flat tabs 42, 44 which are parallel and whose ends are curved in a direction opposite to the lateral tabs 36, 38, these two radial tabs 42. , 44 being spaced from each other ( Figures 4A and 4B).
- 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.
- the jumper 32 For mounting a jumper 32 on an ear 26 of the fan disk 10, the jumper 32 is positioned on the disk 10 so that the radial tabs 42, 44 extend along a rib 12 of the disk 10 and to the upstream of the disc 10.
- the rider 32 is then translated downstream so that the U-bends 41 of the lateral tabs 36, 38 fit on the longitudinal stops 30 of the radial lug 26 of the disc 10 , the transverse wall 34 of the rider 32 coming to be applied on the upstream radial face of the radial lug 26.
- a fixing screw 46 is then inserted from the downstream into the aligned orifices of the rider 32, the lug 26 and the annular flange 48 of the low pressure compressor rotor.
- a fixing nut 50 is clamped on the upstream face of the rider 32 (FIG. 5).
- 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.
Abstract
Description
Claims
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 true EP2531700A1 (fr) | 2012-12-12 |
EP2531700B1 EP2531700B1 (fr) | 2013-12-25 |
Family
ID=42733744
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11705644.0A Active EP2531700B1 (fr) | 2010-02-04 | 2011-01-21 | Soufflante de turbomachine |
Country Status (9)
Country | Link |
---|---|
US (1) | US9376925B2 (fr) |
EP (1) | EP2531700B1 (fr) |
JP (1) | JP5674818B2 (fr) |
CN (1) | CN102753788B (fr) |
BR (1) | BR112012018267B1 (fr) |
CA (1) | CA2786988C (fr) |
FR (1) | FR2955904B1 (fr) |
RU (1) | RU2555099C2 (fr) |
WO (1) | WO2011095722A1 (fr) |
Families Citing this family (1)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2303148A (en) * | 1941-03-24 | 1942-11-24 | Tinnerman Products Inc | Nut fastened installations |
BE499742A (fr) * | 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 |
-
2010
- 2010-02-04 FR FR1000456A patent/FR2955904B1/fr active Active
-
2011
- 2011-01-21 WO PCT/FR2011/050116 patent/WO2011095722A1/fr active Application Filing
- 2011-01-21 CN CN201180008540.9A patent/CN102753788B/zh active Active
- 2011-01-21 BR BR112012018267-6A patent/BR112012018267B1/pt active IP Right Grant
- 2011-01-21 JP JP2012551662A patent/JP5674818B2/ja active Active
- 2011-01-21 CA CA2786988A patent/CA2786988C/fr active Active
- 2011-01-21 US US13/576,071 patent/US9376925B2/en active Active
- 2011-01-21 EP EP11705644.0A patent/EP2531700B1/fr active Active
- 2011-01-21 RU RU2012137508/06A patent/RU2555099C2/ru active
Non-Patent Citations (1)
Title |
---|
See references of WO2011095722A1 * |
Also Published As
Publication number | Publication date |
---|---|
RU2012137508A (ru) | 2014-03-10 |
WO2011095722A1 (fr) | 2011-08-11 |
US20120294721A1 (en) | 2012-11-22 |
CA2786988A1 (fr) | 2011-08-11 |
FR2955904A1 (fr) | 2011-08-05 |
FR2955904B1 (fr) | 2012-07-20 |
US9376925B2 (en) | 2016-06-28 |
CA2786988C (fr) | 2017-11-14 |
BR112012018267B1 (pt) | 2020-10-13 |
JP5674818B2 (ja) | 2015-02-25 |
BR112012018267A2 (pt) | 2017-06-27 |
JP2013519030A (ja) | 2013-05-23 |
RU2555099C2 (ru) | 2015-07-10 |
CN102753788B (zh) | 2015-02-11 |
CN102753788A (zh) | 2012-10-24 |
EP2531700B1 (fr) | 2013-12-25 |
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