EP0530097A1 - Rotor de turbomachine à positionnement angulaire amélioré des aubes - Google Patents

Rotor de turbomachine à positionnement angulaire amélioré des aubes

Info

Publication number
EP0530097A1
EP0530097A1 EP92402340A EP92402340A EP0530097A1 EP 0530097 A1 EP0530097 A1 EP 0530097A1 EP 92402340 A EP92402340 A EP 92402340A EP 92402340 A EP92402340 A EP 92402340A EP 0530097 A1 EP0530097 A1 EP 0530097A1
Authority
EP
European Patent Office
Prior art keywords
blades
groove
rotor
rim
rotor according
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.)
Withdrawn
Application number
EP92402340A
Other languages
German (de)
English (en)
French (fr)
Inventor
Jacques Marie Pierre Stenneler
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0530097A1 publication Critical patent/EP0530097A1/fr
Withdrawn legal-status Critical Current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 the rotors of turbomachinery or compressors, such as aircraft turbojets. It relates more precisely to the fixing of the blades on the rotor of a turbomachine.
  • the blades are fixed to the rotor in two different ways. They are either fixed in individual cells machined on the periphery of the rotor, or all fixed in the same circular groove machined on the periphery of the rotor. In this case, the blades are commonly called “hammer foot attachment blades". As shown in Figures 1 and 2, such blades 10 therefore have a bulbous-shaped foot 7 which is received in the annular groove 6 machined in a rim 5 of the rotor and whose section corresponds to that of the bulb 7. L the blade is completed with a positioning platform 8 located between the blade 9 and the hammer foot. This platform 8 rests beforehand on an external surface 18 of the rim 5 by a bearing surface 19.
  • FIGS. 3A and 3B illustrate this problem of angular positioning.
  • FIG. 3A three adjacent platforms 8 are shown.
  • the diamond shape implies that the width L of a platform 8 is necessarily greater than the thickness E, that is to say the distance between the two closest sides of the diamond shape or the parallelogram. Therefore, any tendency to pivot for a blade is facilitated by the fact that this pivoting releases additional play. All the vanes can therefore pivot, this pivoting being relative to the shape of the platforms 8.
  • the blades are then immobilized in the groove 6 so as to prevent the bulb 7 of a blade from being facing the notch 14, which would mean expelling the blade from the throat 6.
  • grooves 1, 2 cooperating with circumferential ribs 3, 4, of the rim 5 of the rotor, so that the platforms 6 come into abutment on the grooves 1, 2.
  • the implementation of the grooves 1 and 2 and the ribs 3 and 4 penalizes the design by increasing the thickness of the platform 8 and the height of the disc. It will be noted, moreover, that the lateral play of manufacture remaining between the groove 1 or 2 and the rib 3 or 4 authorizes, in all rigor, the corresponding pivoting of the blade in the groove 6.
  • the object of the invention is to limit the possibilities of pivoting of the blades.
  • the blades are joined two by two at the level of the platforms to form doublets so as to increase, for each of them, the bearing formed by the two hammer feet and thus limit the rotation of the blades by relative to the axes perpendicular to the axis of the rotor.
  • a first method consists in welding or brazing the blades by their platform.
  • a second consists in producing a doublet of blades by foundry.
  • a third solution consists in using machining to produce such a doublet of blades.
  • the invention is particularly applicable to blades whose platforms are lozenges.
  • Figures 4 and 5 symbolize a doublet formed of two adjacent blades and fixed relative to each other.
  • the attachment has been represented by a weld bead 20 which joins the two platforms 8 of the two adjacent blades.
  • This weld bead joins the two platforms in pairs on their long side. In this way, the two blades are fixed relative to each other over the entire length of the parallelogram of the platform 8.
  • the two blades are produced beforehand individually and preferably welded by means of an electron beam.
  • a distance D separates the two blades.
  • this distance D also separates the two bulbs 7 from the hammer feet of each of the two blades.
  • Welding is one of the possibilities of manufacturing doublets. It is also reported that it is possible to consider providing a doublet during the casting of the blades. Such a foundry blank can be machined to obtain the final doublet. It is also possible to produce the doublet only by machining from a common blank for a single doublet.
  • the mounting of a doublet requires the presence of two notches 21 in the groove 13. These two notches are spaced by the same distance D separating the two blades, therefore the two bulbs, from the same doublet . The latter can therefore be introduced into the groove by penetration of the two bulbs in two adjacent notches 21 and by translation of the doublet in the groove.

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)
EP92402340A 1991-08-28 1992-08-26 Rotor de turbomachine à positionnement angulaire amélioré des aubes Withdrawn EP0530097A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9110665A FR2680828A1 (fr) 1991-08-28 1991-08-28 Rotor de turbomachine a positionnement angulaire ameliore des aubes.
FR9110665 1991-08-28

Publications (1)

Publication Number Publication Date
EP0530097A1 true EP0530097A1 (fr) 1993-03-03

Family

ID=9416425

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92402340A Withdrawn EP0530097A1 (fr) 1991-08-28 1992-08-26 Rotor de turbomachine à positionnement angulaire amélioré des aubes

Country Status (3)

Country Link
EP (1) EP0530097A1 (enrdf_load_stackoverflow)
CA (1) CA2077051C (enrdf_load_stackoverflow)
FR (1) FR2680828A1 (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1130217A1 (de) * 2000-03-01 2001-09-05 ABB Alstom Power N.V. Befestigung von Laufschaufeln in einer Turbomaschine
FR2856105A1 (fr) * 2003-06-16 2004-12-17 Snecma Moteurs Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique a l'aide des raidisseurs de plates-formes

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102588003B (zh) * 2012-03-15 2014-12-24 北京航空航天大学 一种低应力双圆弧面直榫连接结构

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB534193A (en) * 1939-01-18 1941-02-28 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbine buckets
FR1536084A (fr) * 1966-12-07 1968-08-09 Gen Electric Structure de support d'aubes de turbine
US4130379A (en) * 1977-04-07 1978-12-19 Westinghouse Electric Corp. Multiple side entry root for multiple blade group
EP0305223A1 (fr) * 1987-06-10 1989-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de verrouillage d'aubes et procédés de montage et de démontage
EP0388286A1 (fr) * 1989-03-15 1990-09-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aubes à pied marteau à positionnement angulaire amélioré

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS595806A (ja) * 1982-07-03 1984-01-12 Nissan Motor Co Ltd 軸流タ−ビンロ−タ

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB534193A (en) * 1939-01-18 1941-02-28 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbine buckets
FR1536084A (fr) * 1966-12-07 1968-08-09 Gen Electric Structure de support d'aubes de turbine
US4130379A (en) * 1977-04-07 1978-12-19 Westinghouse Electric Corp. Multiple side entry root for multiple blade group
EP0305223A1 (fr) * 1987-06-10 1989-03-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de verrouillage d'aubes et procédés de montage et de démontage
EP0388286A1 (fr) * 1989-03-15 1990-09-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aubes à pied marteau à positionnement angulaire amélioré

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 8, no. 90 (M-292)25 Avril 1984 & JP-A-59 005 806 ( NISSAN JIDOSHA ) 12 Janvier 1984 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1130217A1 (de) * 2000-03-01 2001-09-05 ABB Alstom Power N.V. Befestigung von Laufschaufeln in einer Turbomaschine
FR2856105A1 (fr) * 2003-06-16 2004-12-17 Snecma Moteurs Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique a l'aide des raidisseurs de plates-formes
EP1489266A1 (fr) * 2003-06-16 2004-12-22 Snecma Moteurs Rétention d'une aube avec attache à pied de marteau dissymétrique à l'aide des raidisseurs de plates-formes
US7080974B2 (en) 2003-06-16 2006-07-25 Snecma Moteurs Retention capacity of a blade having an asymmetrical hammerhead fastener, with the help of platform stiffeners

Also Published As

Publication number Publication date
FR2680828A1 (fr) 1993-03-05
FR2680828B1 (enrdf_load_stackoverflow) 1995-02-03
CA2077051C (fr) 2000-11-14
CA2077051A1 (fr) 1993-03-01

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