EP1223309B1 - Système de rétention des aubes de type combine ou cascade - Google Patents

Système de rétention des aubes de type combine ou cascade Download PDF

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Publication number
EP1223309B1
EP1223309B1 EP02290048A EP02290048A EP1223309B1 EP 1223309 B1 EP1223309 B1 EP 1223309B1 EP 02290048 A EP02290048 A EP 02290048A EP 02290048 A EP02290048 A EP 02290048A EP 1223309 B1 EP1223309 B1 EP 1223309B1
Authority
EP
European Patent Office
Prior art keywords
disc
flange
radial
cheek
disk
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 - Lifetime
Application number
EP02290048A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1223309A1 (fr
Inventor
Charles Jean-Pierre Douguet
Maurice Guy Judet
Claude Robert Louis Lejars
Thierry Nitre
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 Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1223309A1 publication Critical patent/EP1223309A1/fr
Application granted granted Critical
Publication of EP1223309B1 publication Critical patent/EP1223309B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the present invention relates to a system for semi-collective retention of blades turbojet engines.
  • turbojet fan rotor having a plurality of removable fan blades attached to a rim of a disk, said fan blades each having a blade root which is mounted in a substantially axial groove and corresponding shape, formed in the disc rim, each of the fan blades being held in the groove by a hold placed under each foot of the blade, and means to retain axially the wedges and the blade roots in the grooves, said means comprising in particular a flange bearing against the upstream face of the disk and fixed to said disk by fastening means.
  • the upstream face designates the face directed towards the front of the engine and the downstream face, the one facing the back.
  • a radially inner part designates an area close to the axis of rotation of the disk, and a portion radially outside, the one that is far away.
  • FR A 2 561 307 shows a shim having a spout resting on the dawn foot.
  • the axial retention of the blade root is ensured by a ring placed between the wedge and the teeth of the disc, the ring being in contact with the wedge and the teeth of the disc and held radially in position by a flange.
  • Document FR A 2 681 374 describes a fastening of fan blades of turbojet engine using scalloped flanges arranged upstream and downstream at the periphery of the disk and provided with orifices, intended for fixing two rings provided respectively on a front cover and a compressor drum, which cooperate with the ends of the blade roots to immobilize them axially and radially.
  • the fan blades have on the downstream part of their feet two spoilers which engage respectively on the inner and outer radial faces of a first ring, and also have on the upstream part of their feet two spoilers that engage respectively on the inner and outer radial faces of a second ring.
  • This locking device complicates the machining of the fan blades which present two spoilers at both ends, and makes it difficult and time consuming to replace a damaged blade, because it is necessary to unscrew the plurality of fixing pins of a ring, these pins lodged in the orifices of a scalloped flange and being of a difficult access.
  • the object of the invention is to propose a fan rotor as described in introduction in which the blades are held in cascade in case of displacement axial.
  • the wedges comprising one of their ends a protrusion, said protrusion is interposed between the blade roots and the flange, by the the disk has on its upstream face a plurality of radial protuberances alternating with the grooves, in that the flange comprises on its downstream face a plurality of radial teeth arranged opposite and downstream of the radial protuberances (26) of the disk (10), and in that the means for fixing the flange on the disk are arranged in the radially inner portion of the flange.
  • the retention reliability of the fan blades is significantly increased.
  • the fan blades are stopped cascading from the following way: the blade of fan first relies on the hold, then at least one radial tooth of the flange co-operates in part with a protuberance of the disc for immobilize the dawn of blower.
  • the fastening means of the flange contribute to the final stop of the fan blade.
  • the radial protuberances of the disc extend towards the outside, and the radial teeth of the flange extend inwards.
  • said radial protuberances of the disc extend towards the inside and said radial teeth of the flange to the outside.
  • an axial clearance is formed between the radial protuberances of the disk and the radial teeth of the flange.
  • This game helps dissipate some of the energy when the fan blade, retained by the wedge, moves axially.
  • the means for fixing the flange on the disk have a plurality of pins parallel to the axis of rotation of the disk.
  • pins are sufficient in number to retain the flange on the disk in case axial displacement of a fan blade.
  • they comprise a screw-nut assembly accommodating axial forces and shear forces.
  • FIGS. 1 and 2 show a fan rotor disk 10 comprising a rim 12 which has at its periphery a plurality of substantially axial grooves 14 and regularly spaced around the axis of rotation of the disk 10.
  • each groove 14 is axially slidably mounted a foot 16 of a fan blade 18. Between the blade root 16 and the bottom of the groove 14 is engaged a shim 20 which keeps the blade root 16 in abutment against the walls of the groove 14 corresponding.
  • Each shim 20 has an outgrowth 22 at one of its ends.
  • this protrusion 22 is located at the upstream end of the shim 20, between the upstream face of the blade root 16 and a flange 24 bearing against the upstream face of the 10.
  • the flange 24 is formed by an inner wall of a ferrule which delimits internally the airflow channel through the blower.
  • the disc 10 has on its upstream face and alternately with the grooves 14, a plurality of radial protuberances 26 directed outwardly.
  • the flange 24 has on its downstream face a plurality of radial teeth 28 directed inwards, likely to bear against the radial protuberances 26 of the disk 10.
  • Figure 3 shows that to mount the flange 24 on the disc 10 (position unlocked), the radial teeth 28 of the flange 24 are passed through the notches 30 interposed between the radial protuberances 26 of the disc 10 and located above the bottoms of grooves 14.
  • Figure 4 shows the flange 24 in the locked position.
  • the width of the teeth radial plates 28 of the flange 24 may be greater than that of the radial protuberances 26 of the disc 10, so that a fraction of each of the radial teeth 28 can stall axially a portion of each fan blade 18.
  • the flange 24 is held in position by a simple screw / nut assembly.
  • the fixing means of the flange 24 comprise locking means constituted by pins having screws 44 and nuts 46.
  • FIG. a flange 42 bolted with said screws 44 and said nuts 46 crimped into the disc 10.
  • the disc 10 which is unchanged in its radially outer portion (protuberances radial 26) is thus simpler in shape in its radially inner portion. It is the same with regard to the flange 24.
  • FIG. 6 shows that disk 10 partially presents radially inner a plurality of orifices for holding the flange 24 on the 10. Fixing the flange 24 on the disk 10 is, for example, using a plurality of screws 44 and nuts 46, so as to keep the flange 24 tight on the disk 10 even if an attempt is made to lose a dawn.
  • the semi-collective axial retention of the blades of the fan is made of the following way. In case of displacement of a fan blade 18, it comes into bearing against the protrusion 22 of the wedge 20. A portion of the radial teeth 28 of the flange 24 stops the fan blade 18. A clearance 48 is formed between said radial teeth 28 of the flange 24 and the radial protuberances of the disk 10 to dissipate a portion of the energy during an attempt to lose a fan blade 18, the flange 24 being able to then deform before these radial teeth 28 come to press against the radial protuberances of the disk 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP02290048A 2001-01-11 2002-01-10 Système de rétention des aubes de type combine ou cascade Expired - Lifetime EP1223309B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0100294A FR2819289B1 (fr) 2001-01-11 2001-01-11 Systeme de retention des aubes de type combine ou cascade
FR0100294 2001-01-11

Publications (2)

Publication Number Publication Date
EP1223309A1 EP1223309A1 (fr) 2002-07-17
EP1223309B1 true EP1223309B1 (fr) 2005-06-08

Family

ID=8858676

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02290048A Expired - Lifetime EP1223309B1 (fr) 2001-01-11 2002-01-10 Système de rétention des aubes de type combine ou cascade

Country Status (9)

Country Link
US (1) US20020090300A1 (ja)
EP (1) EP1223309B1 (ja)
JP (1) JP4031247B2 (ja)
CA (1) CA2364128A1 (ja)
DE (1) DE60204486T2 (ja)
ES (1) ES2240665T3 (ja)
FR (1) FR2819289B1 (ja)
RU (1) RU2221169C2 (ja)
UA (1) UA72255C2 (ja)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
JP4807113B2 (ja) * 2006-03-14 2011-11-02 株式会社Ｉｈｉ ファンのダブテール構造
FR2900437B1 (fr) * 2006-04-27 2008-07-25 Snecma Sa Systeme de retention des aubes dans un rotor
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
FR2930595B1 (fr) * 2008-04-24 2011-10-14 Snecma Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
FR2931871B1 (fr) * 2008-05-29 2011-08-19 Snecma Rotor de soufflante pour une turbomachine.
FR2971822B1 (fr) * 2011-02-21 2015-04-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
FR2996584A1 (fr) 2012-10-10 2014-04-11 Snecma Cale pour pied de pale ajouree
CN106224360A (zh) * 2016-07-25 2016-12-14 珠海格力节能环保制冷技术研究中心有限公司 风扇与电机轴安装结构
CN113083537A (zh) * 2021-05-08 2021-07-09 广州极飞科技股份有限公司 离心喷盘、雾化装置和无人设备

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB928349A (en) * 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
FR2561307B1 (fr) * 1984-03-14 1986-09-12 Snecma Dispositif de verrouillage d'aubes de soufflantes
GB2244100A (en) * 1990-05-16 1991-11-20 Rolls Royce Plc Retaining gas turbine rotor blades
FR2663997B1 (fr) * 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
FR2681374B1 (fr) 1991-09-18 1993-11-19 Snecma Fixation d'aube de souflante de turboreacteur.

Also Published As

Publication number Publication date
RU2221169C2 (ru) 2004-01-10
DE60204486T2 (de) 2006-05-11
FR2819289B1 (fr) 2003-07-11
DE60204486D1 (de) 2005-07-14
CA2364128A1 (fr) 2002-07-11
US20020090300A1 (en) 2002-07-11
JP4031247B2 (ja) 2008-01-09
EP1223309A1 (fr) 2002-07-17
JP2002242888A (ja) 2002-08-28
ES2240665T3 (es) 2005-10-16
FR2819289A1 (fr) 2002-07-12
UA72255C2 (uk) 2005-02-15

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