EP1496206B1 - Amélioration de la capacité de rétention d'une aube à attache marteau dissymétrique - Google Patents

Amélioration de la capacité de rétention d'une aube à attache marteau dissymétrique Download PDF

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Publication number
EP1496206B1
EP1496206B1 EP04291705A EP04291705A EP1496206B1 EP 1496206 B1 EP1496206 B1 EP 1496206B1 EP 04291705 A EP04291705 A EP 04291705A EP 04291705 A EP04291705 A EP 04291705A EP 1496206 B1 EP1496206 B1 EP 1496206B1
Authority
EP
European Patent Office
Prior art keywords
upstream
blade
lip
disk
groove
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
EP04291705A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1496206A1 (fr
Inventor
Christophe Follonier
Claude Lejars
Jérome Mace
Bruce Pontoizeau
Patrick 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
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 SAS filed Critical SNECMA SAS
Publication of EP1496206A1 publication Critical patent/EP1496206A1/fr
Application granted granted Critical
Publication of EP1496206B1 publication Critical patent/EP1496206B1/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
    • F01D5/3023—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

Definitions

  • the invention relates to turbomachine bladed disks, arranged in a conical vein, such as those forming the last stages of a low pressure compressor of a double-flow double-flow turbojet engine with a high dilution ratio.
  • the radius of the vein of the primary flow decreases from upstream to downstream in the low pressure compressor.
  • the conicity of this vein is very high in the last stages.
  • the blades of these stages extend obliquely in the vein relative to the plane perpendicular to the axis of rotation of the compressor, that is to say, obliquely with respect to the direction of the centrifugal force.
  • the invention more specifically relates to bladed discs of this type in which the blades are retained by a hammer-type fastener in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom.
  • the grooves form spans on which the flanks of the blade roots are supported during operation of the turbomachine, these bearing surfaces supporting reaction forces whose resultant is preferably in the plane of centrifugal forces.
  • EP 0 695 856 proposed an asymmetrical hammer clip, that is to say that the angle of the range of the upstream lip, which has the largest diameter, with respect to a plane perpendicular to the axis of rotation, is greater than 1 angle formed between the range of the downstream lip and said plane.
  • FIG. 4B of this document shows the blade-disk connection in the case where the blade, subjected to important axial stresses, pivots about the center of rotation C, constituted by the end of the range of the downstream lip.
  • the figure 1 reproduces Figure 4A of EP 0 695 856 .
  • 1 represents a blade whose dovetail-shaped foot 2 has an upstream flank 3a and a downstream flank 3b whose surfaces bear on bearing surfaces 4a, 4b of the inner faces of an upstream lip. 5 and a downstream lip which delimit a groove 7 formed at the periphery of a disc 12 and whose bottom 8 is connected to the bearing surfaces 4a and 4b by rounded surfaces 9a and 9b respectively.
  • the span 4a of the upstream lip 5 is located inside the geometric circle (C), and the surfaces common to the geometric circle (C) and the section of the upstream lip 5, by a plane containing the axis of rotation. of the disk, are in the form of a crescent having a maximum thickness e.
  • the object of the invention is to improve the retention capacity of an asymmetrical hammer blade of the type described above.
  • the invention more specifically relates to a method for improving the retention capacity of an asymmetrical hammer blade which extends in a conical vein and whose foot is retained in a peripheral groove of a disc, said groove having a lip upstream and a downstream lip having spans that extend in asymmetrical planes with respect to a plane perpendicular to the axis of rotation of said disk and on which the surfaces of the upstream and downstream sides of said foot are supported, the range of said upstream lip being connected to the bottom of said groove by a rounded surface and the upstream flank having in the vicinity of said rounded surface a heel located inside a geometric circle (C) of radius (R) centered on the axis of possible pivoting of said blade due to an axial bias, said geometric circle (C) cutting in the upstream lip a crescent of thickness e.
  • the section of the material removed from the disc 12 in the connection zone 9a between the bearing surface 4a of the upstream lip 5 and the bottom 8 of the groove 7 is represented by reference 20.
  • This material can be removed for example by milling , or by grinding.
  • This removal of material increases the space available under the heel 11 of the blade according to the prior art and makes it possible to replace the blade shown in FIG. figure 1 by a new dawn 30 shown on the figure 3 which has a heel 31, larger than the heel 11 of the blade according to the prior art.
  • This dawn 31 is, apart from the heel 31, identical to the dawn 1.
  • the dotted line on the figure 3 shows the section of the dawn according to the prior art.
  • the point 32 of the heel 31, the farthest from the center of rotation C is distant from this center by a distance R1 greater than R, and the geometric circle (C1) of center C and radius R1 cuts in the lip 5 a crescent which has a thickness e1 greater than that of the crescent shown on the figure 1 , which substantially improves the retention capacity of the modified blade 1 in the modified groove of the disk 12.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Percussive Tools And Related Accessories (AREA)
  • Food-Manufacturing Devices (AREA)
EP04291705A 2003-07-07 2004-07-06 Amélioration de la capacité de rétention d'une aube à attache marteau dissymétrique Expired - Lifetime EP1496206B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308295A FR2857405B1 (fr) 2003-07-07 2003-07-07 Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique
FR0308295 2003-07-07

Publications (2)

Publication Number Publication Date
EP1496206A1 EP1496206A1 (fr) 2005-01-12
EP1496206B1 true EP1496206B1 (fr) 2008-04-30

Family

ID=33443241

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291705A Expired - Lifetime EP1496206B1 (fr) 2003-07-07 2004-07-06 Amélioration de la capacité de rétention d'une aube à attache marteau dissymétrique

Country Status (9)

Country Link
US (1) US7029237B2 (ru)
EP (1) EP1496206B1 (ru)
JP (1) JP4047837B2 (ru)
CA (1) CA2472299C (ru)
DE (1) DE602004013400T2 (ru)
ES (1) ES2305684T3 (ru)
FR (1) FR2857405B1 (ru)
RU (1) RU2346165C2 (ru)
UA (1) UA85164C2 (ru)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2861128B1 (fr) * 2003-10-16 2007-06-08 Snecma Moteurs Dispositif d'attache d'une aube mobile sur un disque de rotor de turbine dans un turbomachine
FR2886336B1 (fr) * 2005-05-26 2007-08-24 Snecma Moteurs Sa Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes
EP1801355B1 (fr) * 2005-12-23 2015-02-11 Techspace Aero Dispositif pour bloquer les aubes d'un disque de turbomachine
KR101014797B1 (ko) * 2008-08-07 2011-02-15 김병길 이중 바닥 배선용 현수식 시스템 박스
GB201416505D0 (en) 2014-09-18 2014-11-05 Rolls Royce Plc Gas turbine engine
GB201502612D0 (en) * 2015-02-17 2015-04-01 Rolls Royce Plc Rotor disc
US10683765B2 (en) * 2017-02-14 2020-06-16 General Electric Company Turbine blades having shank features and methods of fabricating the same
CN114451680B (zh) * 2021-01-19 2024-03-19 江西阳光安全设备集团有限公司 一种除尘低噪音型密集架

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
GB2097480B (en) * 1981-04-29 1984-06-06 Rolls Royce Rotor blade fixing in circumferential slot
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement
FR2723397B1 (fr) * 1994-08-03 1996-09-13 Snecma Disque de compresseur de turbomachine muni d'une gorge circulaire asymetrique

Also Published As

Publication number Publication date
JP4047837B2 (ja) 2008-02-13
US7029237B2 (en) 2006-04-18
RU2346165C2 (ru) 2009-02-10
JP2005030395A (ja) 2005-02-03
FR2857405B1 (fr) 2005-09-30
DE602004013400T2 (de) 2009-05-07
CA2472299A1 (fr) 2005-01-07
FR2857405A1 (fr) 2005-01-14
ES2305684T3 (es) 2008-11-01
DE602004013400D1 (de) 2008-06-12
UA85164C2 (ru) 2009-01-12
CA2472299C (fr) 2012-10-16
EP1496206A1 (fr) 2005-01-12
RU2004120675A (ru) 2006-01-10
US20050008491A1 (en) 2005-01-13

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