EP2705256B1 - Rotor de turbomachine avec moyen de retenue axiale des aubes - Google Patents

Rotor de turbomachine avec moyen de retenue axiale des aubes Download PDF

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Publication number
EP2705256B1
EP2705256B1 EP12725108.0A EP12725108A EP2705256B1 EP 2705256 B1 EP2705256 B1 EP 2705256B1 EP 12725108 A EP12725108 A EP 12725108A EP 2705256 B1 EP2705256 B1 EP 2705256B1
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EP
European Patent Office
Prior art keywords
axial
rotor according
platforms
blades
wedges
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
EP12725108.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2705256A1 (fr
Inventor
François Marie Paul Marlin
Frédéric IMBOURG
Didier QUEANT
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
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Safran Aircraft Engines SAS
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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Definitions

  • the present invention relates to the field of turbomachines, more particularly that of multi-stream turbofan engines with a front blower and aims at the axial locking of the blades housed in grooves or axial cavities on the rim of a rotor disc. It essentially aims to lock the blades of the fan in their housing on the fan disk.
  • a multitrack turbojet engine comprises a gas turbine engine driving a fan generally at the front of the engine.
  • a blower conventionally comprises a rotor disk provided with a plurality of radial fan blades spaced from each other circumferentially and fixed in individual cells formed on its rim.
  • the cells are oriented substantially axially and are section dovetail. Their shape is complementary to that of the blade roots to ensure their retention in place when the blades are subjected to centrifugal forces during the rotation of the disc.
  • the vanes are mounted individually by being introduced axially into the cells. They are wedged radially by means of an axial wedge that is slid between the bottom of the cell and the foot of the blade.
  • abutment which is generally constituted by the drum of the low pressure rotor or booster which is secured to the fan disk downstream and upstream by means of a lock. Upstream and downstream are defined by the direction of flow of the gas stream through the engine.
  • the latch is formed of a U-shaped piece placed in a radial plane perpendicular to the axial wedge and is itself retained in radial notches formed both in the foot of the blade and in the flanks of the cell.
  • the axial blade retainer is formed of an axial wedge disposed under the root of the blade in the bottom of the cell and a latch perpendicular to the axial wedge against which the root of the blade comes into axial stop at the upstream.
  • the latch is disposed in radial notches in the flanks of the disc teeth - the portion of the rim of the disc between two adjacent cells is designated tooth.
  • the latch and the wedge are secured to one another by a screw which passes radially through a first tab extending the axial wedge upstream and a second tab secured to the latch, at right angles thereto.
  • a spacer is inserted between the latch and the root of the blade to damp the axial forces resulting from an impact on the blades of the fan produced by the ingestion of an object for example.
  • the spacer is made of a deformable material, such as a honeycomb, to absorb the energy of the shock.
  • the vanes In a fan rotor. the vanes comprise a blade and a foot for mounting on the disk but no integrated platform. Inter-blade platforms are reported between the blades to ensure continuity of the radially inner surface of the air stream passing through the rotor. These inter blade platforms, when they are metallic, are fixed on the teeth of the disk rim by axial pins passing through two axial eyelets integral with one of the tooth, the other of the inter-blade platform.
  • the fan blades large rope and composite material fitted to some engines, are immobilized by axial shims, arranged under their foot in the form of a bulb, which are also composite material.
  • the axial shims are immobilized by a screw connection with the axial retention lock upstream of the blade. This connection occupies a large space between the upstream edge of the disc teeth, as seen on the figure 1 .
  • the size of the screw connection between the wedge and the lock thus requires a bypass of the area by the rear shell of the upstream cover of the rotor.
  • the upstream cowl is the fairing piece that forms the upstream outer surface of the fan rotor.
  • the cantilever of the wedge relative to the upstream face of the lock does not pose any particular problem and is acceptable because it finds a place in the downstream volume formed by the hood rear ferrule.
  • inter blade platforms are composite box
  • the rear part of such a cover has no mechanical strength and can not provide this maintenance function.
  • Such a ferrule must then be festooned and be sufficiently cleared not to interfere and leave the passage to the axial wedges.
  • the axial shim being of composite material such as fan blades; it is then necessary to stick a light alloy metal head to ensure the connection by screw with the lock. The hold is then more difficult to manufacture.
  • the object of the invention is to provide a fan rotor that does not have the disadvantages of the above solution.
  • the turbojet fan rotor comprises a disk with a rim and substantially axial cells with a dovetail section on the rim, and vanes mounted individually in the cells, and internal platforms.
  • the solution of the invention therefore consists in eliminating the nut-type connection between the axial shim and the lock.
  • the inter blade blades are held in place by means of an upstream retaining ferrule platforms inter blades.
  • this ferrule forms said transverse annular piece against which the axial shims abut.
  • the axial wedge comprises a radial tab forming axial abutment against said upstream ferrule; more particularly, the lock comprises an axial tab forming an axial stop for the axial wedge.
  • the lock comprises a spacer of material capable of being deformed by compression between the latch and the root of the blade.
  • the rotor comprising inter blade platforms held in place by means of a retaining shell of the inter-blade platforms, said annular piece for immobilizing the axial shims forms an upstream protective cone of the rotor.
  • the support ring of the platforms comprises a radial flange for attachment to the disk of the rotor, the flange being scalloped to provide openings through which the axial shims abut axially against the transverse annular piece.
  • the axial shims comprise an axial lug with a radial orifice by means of which the axial shims can be extracted from their cell.
  • the invention also relates to the turbofan engine comprising a fan rotor thus defined.
  • the turbojet 1 of the figure 1 is a double flow with a front blower 2 comprising a fan disk 4 on which are disposed fan blades 6 retained by their foot in cells formed on the rim.
  • the disk is cantilevered on the low pressure shaft which also supports the drum 7 of the booster or low pressure compressor immediately downstream of the disk and to which it is attached.
  • a piece 5 of generally conical shape is attached upstream on the fan disk; this piece has an essentially aerodynamic function of guiding the air flow towards the engine inlet.
  • FIGS. 2 and 3 show the mounting of a blade 6 of a fan in a cavity 41 of the disk of the fan, according to the prior art.
  • An axial shim 43 is slid under the root of the blade so as to ensure the radial retention of the blade in its cell and a latch 44 perpendicular to the shim 43 is slid into notches in the sides of the cell of the upstream side of the disc.
  • the axial shim comprises a portion 43a which is housed in the cell and an upstream end tab 43b which projects beyond the disk 4 and serves for connection with the lock 44.
  • the connection is provided by a screw 45 which passes through the both the tab 43b and a tab 44a secured to the lock.
  • connection mode has a certain size and interferes with the mounting of the cover 5.
  • the cover 5 comprises a rib 51 with a radial flange through which it is fixed to the disk 4.
  • the outer rear edge 52 axially blocks the inter blade platforms 8 on the disk which are held radially elsewhere.
  • FIGS. 4 and 5 illustrate a first embodiment. Disk 4 and the blades are not modified.
  • An axial shim 143 is slid under the foot of the blade 6 in the space available between the root of the blade and the bottom of the cell.
  • The comprises an axial portion 143a under the blade and a tab 143b which extends upstream, a tab 143c radial ends the tab upstream and axial stop shape.
  • a transverse latch 144 here perpendicular to the axial wedge, is slid into notches formed in the sides of the cell.
  • a tab 144a at right angles to the latch extends upstream to abut against the radial tab 143c of the axial spacer 143.
  • a spacer 144b, honeycomb, is interposed between the latch 144 and the foot of the dawn, according to a known solution as such of the prior art.
  • the inter blade blades 8 ' are held in place, in retention with respect to the centrifugal forces, by a collar 145 which comprises an annular portion 145b which is supported on a corresponding locking lug 8' a, provided on the platforms inter blade 8 '.
  • the outer surface of the annular portion 145b of the shell 145 forms a continuous aerodynamic surface with that of the inter blade blades 8 '.
  • a radial flange 145a is pierced with orifices, not shown, through which the shell is bolted to the front face of the teeth 42. This radial flange also forms an axial stop for the tabs 143c.
  • the cone 5 Upstream of the shell 145, the cone 5 'bears against the upstream face thereof; it is fixed to the disc 4 by any appropriate means.
  • the assembly of the assembly comprises the installation of the vanes, their locking by the locks that slide in the radial notches, the introduction of axial shims 143 under the vanes, possibly with the aid of a mallet. because of the tight fit that is required.
  • the tongue 143c abuts against the tab 144a.
  • the latch 144 comprises bearing surfaces cooperating with the notches for a radial wedging when it is supported on the shim 143.
  • the establishment of the annular shroud 145 locks the assembly, bearing against the upstream face of the tongue 143c .
  • the axial wedge 243 comprises an axial portion 243a, which is placed between the root of the blade and the bottom of the cell, and an upstream leg 243b which is here right without radial return.
  • a latch 244 retains the blade axially as the previous latch 144;
  • an annular ferrule 245 for centrifugal retention of inter-blade platforms comprises an annular support portion on upstream legs formed on the inter-blade platforms.
  • a radial flange 245a is bolted to the teeth of the rim of the disc 4 and ensures the maintenance of the ferrule on the disc. This ferrule is distinguished from the preceding ferrule by the fact that it does not fulfill the function of axial wedging of the wedges 243.
  • the vanes 6 are placed in their respective cells with the corresponding axial locking latch 244 and then the axial spacers 243 are slid between the root of the blades and the bottom of the cells.
  • the ferrule 245 is bolted (46) to the rim teeth.
  • the openings 245a1 clear the end of the legs 243b as seen on the figure 7 .
  • the rib 5" has bears against the tab 243b which is thereby retained against any displacement upstream, in operation of the engine.
  • One or other of the two embodiments allows the realization of axial shims made of a composite material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12725108.0A 2011-05-04 2012-05-04 Rotor de turbomachine avec moyen de retenue axiale des aubes Active EP2705256B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1153839A FR2974864B1 (fr) 2011-05-04 2011-05-04 Rotor de turbomachine avec moyen de retenue axiale des aubes
PCT/FR2012/051004 WO2012150425A1 (fr) 2011-05-04 2012-05-04 Rotor de turbomachine avec moyen de retenue axiale des aubes

Publications (2)

Publication Number Publication Date
EP2705256A1 EP2705256A1 (fr) 2014-03-12
EP2705256B1 true EP2705256B1 (fr) 2017-02-08

Family

ID=46201730

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12725108.0A Active EP2705256B1 (fr) 2011-05-04 2012-05-04 Rotor de turbomachine avec moyen de retenue axiale des aubes

Country Status (9)

Country Link
US (1) US9441494B2 (ja)
EP (1) EP2705256B1 (ja)
JP (1) JP6027606B2 (ja)
CN (1) CN103502653B (ja)
BR (1) BR112013028170B1 (ja)
CA (1) CA2834759C (ja)
FR (1) FR2974864B1 (ja)
RU (1) RU2607986C2 (ja)
WO (1) WO2012150425A1 (ja)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3004227B1 (fr) * 2013-04-09 2016-10-21 Snecma Disque de soufflante pour un turboreacteur
FR3010442B1 (fr) * 2013-09-09 2015-10-09 Snecma Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef
US11220920B2 (en) * 2014-04-07 2022-01-11 Safran Aircraft Engines Turbine engine rotor lock
US10371163B2 (en) * 2016-02-02 2019-08-06 General Electric Company Load absorption systems and methods
FR3048997B1 (fr) * 2016-03-21 2020-03-27 Safran Aircraft Engines Plateforme d'aube et disque de soufflante de turbomachine aeronautique
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
FR3102796B1 (fr) 2019-10-30 2021-10-08 Safran Aircraft Engines Plateformes inter-aubes
FR3116573B1 (fr) 2020-11-20 2023-03-24 Safran Aircraft Engines Aube comprenant un bouclier ayant une conduite de passage d’air de dégivrage

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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
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
FR2639402B1 (fr) * 1988-11-23 1990-12-28 Snecma Disque ailete de rotor de turbomachine
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
FR2814495B1 (fr) * 2000-09-28 2003-01-17 Snecma Moteurs Systeme de retention amont pour aubes et plates-formes de soufflante
US6457942B1 (en) 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
US6481971B1 (en) * 2000-11-27 2002-11-19 General Electric Company Blade spacer
FR2841609B1 (fr) * 2002-06-27 2004-09-10 Snecma Moteurs Cale de retenue du pied des aubes de soufflante
FR2844562B1 (fr) * 2002-09-18 2004-10-29 Snecma Moteurs Maitrise de la position axiale d'une aube de rotor de soufflante
FR2889264B1 (fr) 2005-07-29 2007-11-02 Snecma Verrouillage des aubes dans un rotor de soufflante
FR2913734B1 (fr) * 2007-03-16 2009-05-01 Snecma Sa Soufflante de turbomachine
FR2931871B1 (fr) * 2008-05-29 2011-08-19 Snecma Rotor de soufflante pour une turbomachine.
RU87212U1 (ru) * 2009-04-07 2009-09-27 Российская Федерация, От Имени Которой Выступает Министерство Промышленности И Торговли Российской Федерации Рабочее колесо вентилятора или компрессора
AU2013220464A1 (en) * 2012-02-13 2014-09-04 Cosmo Technologies Limited Method for treating intestinal diseases presenting at least one inflammatory component

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Also Published As

Publication number Publication date
JP6027606B2 (ja) 2016-11-16
RU2607986C2 (ru) 2017-01-11
JP2014513765A (ja) 2014-06-05
CA2834759A1 (fr) 2012-11-08
FR2974864B1 (fr) 2016-05-27
CN103502653A (zh) 2014-01-08
FR2974864A1 (fr) 2012-11-09
WO2012150425A1 (fr) 2012-11-08
BR112013028170B1 (pt) 2021-03-23
EP2705256A1 (fr) 2014-03-12
BR112013028170A2 (pt) 2017-01-10
US9441494B2 (en) 2016-09-13
US20140072437A1 (en) 2014-03-13
CN103502653B (zh) 2016-10-26
CA2834759C (fr) 2019-01-08
RU2013150342A (ru) 2015-06-10

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