EP0388286A1 - Blades with hammer-type feet for improved angular positioning - Google Patents

Blades with hammer-type feet for improved angular positioning Download PDF

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Publication number
EP0388286A1
EP0388286A1 EP90400670A EP90400670A EP0388286A1 EP 0388286 A1 EP0388286 A1 EP 0388286A1 EP 90400670 A EP90400670 A EP 90400670A EP 90400670 A EP90400670 A EP 90400670A EP 0388286 A1 EP0388286 A1 EP 0388286A1
Authority
EP
European Patent Office
Prior art keywords
blade
groove
blades
stilt
disc
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
Application number
EP90400670A
Other languages
German (de)
French (fr)
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EP0388286B1 (en
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 EP0388286A1 publication Critical patent/EP0388286A1/en
Application granted granted Critical
Publication of EP0388286B1 publication Critical patent/EP0388286B1/en
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 present invention relates to the fixing of the blades on the rotor discs of turbomachinery
  • the solution used to fix the blades in the rotor disc consists in having blades known as hammer, that is to say in the shape of a bulb which is housed in a circumferential groove of the disc rim whose section corresponds to that of the bulb.
  • FIGS. 1 and 2 of the present application which reflects a first solution according to the current state of the art, blades had been made comprising on the internal face of their platform grooves 1, 2 which cooperated with circumferential ribs 3, 4 of the rim 5 of the disc so that the platforms abut on the disc.
  • This solution has the disadvantage of requiring the thickening of the platform and the widening of the rim of the disc.
  • the present invention provides a remedy for these drawbacks by providing a solution which ensures good circumferential guidance of the blade while avoiding the use of rim ribs and the corresponding grooves of the disc, or platforms with circular edges. .
  • the subject of the invention is therefore a mounting device with improved angular positioning of hammer foot vanes in a compressor or turbine rotor, the rim of the rotor disc comprising a circumferential groove opening out on the circumference of the disc in a groove of reduced width, groove in which blades are maintained comprising a blade fixed on a rectangular platform extended by a stilt at the end of which is fixed, according to the longitudinal plane of symmetry of the platform, a bulbous foot of reduced circumferential width capable of cooperating with the groove, characterized in that the stilt of the blade extends over the entire circumferential width of the blade and cooperates with the groove of the rim of the disc to guide the blade.
  • the blade has a blade 6 and a platform 7 under which is machined, or come from the foundry, a bulb 8 forming the foot blade intended to secure the shaft in the corresponding groove 9 of the disc.
  • the bulb 8 is connected to the platform 7 by a stilt 10 which crosses the groove 11, of reduced width which opens out from the groove 9 towards the periphery of the rim of the disc.
  • the stilt 10 is extended on either side of the bulb 8, over the entire circumferential width of the blade so that the upstream face 10a and the downstream face 10b cooperate with the internal edges of the circumferential groove 11 of the rim and provide precise guidance of the blade on the disc, the guidance being greatly improved by the fact that it is exerted over the entire circumferential width of the blade.
  • the stilt has over its entire length, that is to say over the entire circumferential width of the platform, a constant radial height and guidance is provided over this entire length.
  • recesses 12 have been made in the stilt 10 on each side of the bulb so that only bosses 110 remain at each end of the platform.
  • the quality of the dawn guidance is respected while providing additional lightening of the dawn.
  • the invention finds its interest in compressors of turbomachines, in particular at high pressure, of small diameter and of small pitch.

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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)

Abstract

The blades with a hammer-type fastening have a batten (10) which extends over the entire circumferential width of the blade and which interacts with the groove of the rim (5) of the disc in order to ensure the guidance of the blade. <??>The invention is used for turbo engine compressors. <IMAGE>

Description

La présente invention a pour domaine la fixation des aubes sur les disques de rotors des turbomachinesThe present invention relates to the fixing of the blades on the rotor discs of turbomachinery

Sur les étages de compresseurs de petit diamètre, la solution employée pour fixer les aubes dans le disque du rotor consiste à avoir des aubes à pied dit marteau, c'est à dire en forme de bulbe qui vient se loger dans une gorge circonférentielle de la jante du disque dont la section correspond à celle du bulbe.On the stages of small diameter compressors, the solution used to fix the blades in the rotor disc consists in having blades known as hammer, that is to say in the shape of a bulb which is housed in a circumferential groove of the disc rim whose section corresponds to that of the bulb.

Dans les moteurs les plus modernes, le nombre des aubes a été augmenté, ce qui a nécessité la réduction du pas relatif des aubes et pour y parvenir a amené à réaliser des plates-formes en losange en lieu et place des plates-­formes rectangulaires antérieures.In the most modern engines, the number of blades was increased, which required the reduction of the relative pitch of the blades and to achieve this led to the production of diamond platforms in place of the previous rectangular platforms .

Avec ces plates-formes en losange, la position du centre de poussée aérodynamique sur la pale correspond à un moment oui a tendance à faire pivoter l'aube dans la gorge. Cette tendance est encore accentuée par la présence de jeux circonférentiels entre les plates-formes pour tenir compte des tolérances sur leur largeur et par l'augmentation du jeu de base résultant de ce pivotement naturel de l'aube.With these diamond-shaped platforms, the position of the aerodynamic thrust center on the blade corresponds to a yes moment, which tends to rotate the blade in the groove. This trend is further accentuated by the presence of circumferential clearances between the platforms to take account of the tolerances over their width and by the increase in the basic clearance resulting from this natural pivoting of the blade.

Le pivotement est bien entendu contrecarré par le bulbe dont les flancs actifs viennent en contact avec les flancs de la gorge du disque sous l'effet du champ centrifuge. Cependant pendant la phase de démarrage, les efforts centrifuges ne sont pas suffisants pour empêcher tout pivotement de l'aube ce qui a pour conséquence une portée non homogène du bulbe dans la gorge et des variations dans le calage des aubes.The pivoting is of course counteracted by the bulb, the active sides of which come into contact with the sides of the groove of the disc under the effect of the centrifugal field. However, during the start-up phase, the centrifugal forces are not sufficient to prevent any pivoting of the blade, which results in a non-uniform bearing of the bulb in the groove and variations in the setting of the blades.

Pour éviter ce pivotement, l'état de la technique a mis en oeuvre diverses solutions. Ainsi, comme le montrent les figures 1 et 2 de la présente demande, qui reflète une première solution selon l'état actuel de la technique on avait réalisé des aubes comportant sur la face interne de leur plate-forme des rainures 1, 2 qui coopéraient avec des nervures circonférentielles 3, 4 de la jante 5 du disque afin que les plates-formes viennent en butée sur le disque. Cette solution a pour inconvénient de nécessiter l'épaississement de la plate-forme et l'élargissement de la jante du disque.To avoid this pivoting, the state of the art has implemented various solutions. Thus, as shown in FIGS. 1 and 2 of the present application, which reflects a first solution according to the current state of the art, blades had been made comprising on the internal face of their platform grooves 1, 2 which cooperated with circumferential ribs 3, 4 of the rim 5 of the disc so that the platforms abut on the disc. This solution has the disadvantage of requiring the thickening of the platform and the widening of the rim of the disc.

La présente invention apporte un remède à ces inconvénients en procurant une solution qui assure un bon guidage circonférentiel de l'aube tout en évitant le recours à des nervures de la jante et aux rainures correspondantes du disque, ou à des plates-formes à bord circulaire.The present invention provides a remedy for these drawbacks by providing a solution which ensures good circumferential guidance of the blade while avoiding the use of rim ribs and the corresponding grooves of the disc, or platforms with circular edges. .

L'invention a donc pour objet un dispositif de montage à positionnement angulaire amélioré d'aubes à pied marteau dans un rotor de compresseur ou de turbine, la jante du disque de rotor comportant une gorge circonférentielle débouchant sur la circonférence du disque en une rainure de largeur réduite, gorge dans laquelle sont maintenues des aubes comportant une pale fixée sur une plate-forme rectangulaire prolongée par une échasse à l'extrémité de laquelle est fixé, selon le plan de symétrie longitudinal de la plate-forme un pied en forme de bulbe de largeur circonférentielle réduite susceptible de coopérer avec la gorge, caractérisé en ce que l'échasse de l'aube s'étend sur toute la largeur circonférentielle de l'aube et coopère avec la rainure de la jante du disque pour assurer le guidage de l'aube.The subject of the invention is therefore a mounting device with improved angular positioning of hammer foot vanes in a compressor or turbine rotor, the rim of the rotor disc comprising a circumferential groove opening out on the circumference of the disc in a groove of reduced width, groove in which blades are maintained comprising a blade fixed on a rectangular platform extended by a stilt at the end of which is fixed, according to the longitudinal plane of symmetry of the platform, a bulbous foot of reduced circumferential width capable of cooperating with the groove, characterized in that the stilt of the blade extends over the entire circumferential width of the blade and cooperates with the groove of the rim of the disc to guide the blade.

D'autres caractéristiques seront explicitées en regard des figures annexées parmi lesquelles

  • - la figure 1 représente le premier exemple de l'état de la technique mentionné plus haut et dont il ne sera plus fait état dans la suite du texte.
  • - la figure 2 est une vue perspective de dessous d'une aube selon l'état de la technique de la figure 1.
  • - la figure 3 montre en coupe longitudinale partielle (c'est à dire en coupe passant par l'axe du compresseur) la jante d'un disque et la forme du pied d'aube correspondant à l'invention.
  • - la figure 4 en est une coupe transversale à l'axe du disque, donc dans le plan du disque
  • - la figure 5 est une vue en perspective similaire à la figure 2, d'une première variante de réalisation de l'invention.
  • - la figure 6 est une vue similaire d'une seconde variante de l'invention.
Other characteristics will be explained with reference to the appended figures, among which
  • - Figure 1 shows the first example of the state of the art mentioned above and which will not be discussed in the following text.
  • - Figure 2 is a perspective view from below of a blade according to the prior art of Figure 1.
  • - Figure 3 shows in partial longitudinal section (ie in section passing through the axis of the compressor) the rim of a disc and the shape of the blade root corresponding to the invention.
  • - Figure 4 is a cross section of the axis of the disc, so in the plane of the disc
  • - Figure 5 is a perspective view similar to Figure 2, of a first alternative embodiment of the invention.
  • - Figure 6 is a similar view of a second variant of the invention.

En regard des figures 3, 4 et 5, on voit que l'aube comporte une pale 6 et une plate-forme 7 sous laquelle est usiné, ou venu de fonderie, un bulbe 8 formant le pied d'aube destiné à assurer le blocage de l'arbre dans la gorge 9 correspondante du disque.With reference to FIGS. 3, 4 and 5, it can be seen that the blade has a blade 6 and a platform 7 under which is machined, or come from the foundry, a bulb 8 forming the foot blade intended to secure the shaft in the corresponding groove 9 of the disc.

Le bulbe 8 est relié à la plate-forme 7 par une échasse 10 qui traverse la rainure 11, de largeur réduite qui débouche de la gorge 9 vers la périphérie de la jante du disque.The bulb 8 is connected to the platform 7 by a stilt 10 which crosses the groove 11, of reduced width which opens out from the groove 9 towards the periphery of the rim of the disc.

Selon l'invention l'échasse 10 est prolongée de part et d'autre du bulbe 8, sur toute la largeur circonférentielle de l'aube de sorte que la face amont 10a et la face aval 10b coopèrent avec les bords internes de la rainure circonférentielle 11 de la jante et assurent un guidage précis de l'aube sur le disque, le guidage étant largement amélioré du fait qu'il s'exerce sur toute la largeur circonférentielle de l'aube.According to the invention the stilt 10 is extended on either side of the bulb 8, over the entire circumferential width of the blade so that the upstream face 10a and the downstream face 10b cooperate with the internal edges of the circumferential groove 11 of the rim and provide precise guidance of the blade on the disc, the guidance being greatly improved by the fact that it is exerted over the entire circumferential width of the blade.

Le fait d'assurer ce guidage au moyen des faces 10a, 10b de l'échasse permet de réaliser un gain de masse important par rapport à la solution des figures 1 et 2 et donc de réduire les moments d'inertie des disques équipés de leurs aubes.The fact of ensuring this guidance by means of the faces 10a, 10b of the stilt makes it possible to achieve a significant gain in mass compared to the solution of FIGS. 1 and 2 and therefore to reduce the moments of inertia of the discs equipped with their blades.

Dans la variante de la figure 5 l'échasse a sur toute sa longueur, c'est à dire sur toute la largeur circonfé­rentielle de la plate forme une hauteur radiale constante et le guidage est assuré sur toute cette longueur.In the variant of FIG. 5, the stilt has over its entire length, that is to say over the entire circumferential width of the platform, a constant radial height and guidance is provided over this entire length.

Dans la variante de la figure 6, on a réalisé dans l'échasse 10 des évidements 12 de chaque côté du bulbe de sorte que seuls subsistent des bossages 110 à chaque extrémité de la plate-forme.In the variant of FIG. 6, recesses 12 have been made in the stilt 10 on each side of the bulb so that only bosses 110 remain at each end of the platform.

La qualité du guidage de l'aube est respectée tout en assurant un alègement supplémentaire de l'aube.The quality of the dawn guidance is respected while providing additional lightening of the dawn.

L'invention trouve son intérêt dans les compresseurs de turbomachines, en particulier à haute pression, de petit diamètre et de faible pas.The invention finds its interest in compressors of turbomachines, in particular at high pressure, of small diameter and of small pitch.

Claims (3)

1. Dispositif de montage à positionnement angulaire amélioré d'aubes à pied marteau dans un rotor de compresseur ou de turbine la jante (5) du disque de rotor comportant une gorge circonférentielle (9) débouchant sur la circonférence du disque en une rainure (11) de largeur réduite, gorge dans laquelle sont maintenues des aubes comportant une pale (6) fixée sur une plate-forme rectangulaire (7) prolongée par une échasse (10) à l'extrémité de laquelle est fixé, selon le plan de symétrie longitudinal de la plate-forme un pied en forme de bulbe (8) de largeur circonférentielle réduite susceptible de coopérer avec la gorge (9), caractérisé en ce que l'échasse (10) de l'aube s'étend sur toute la largeur circonférentielle de l'aube et coopère avec la rainure (11) de la jante du disque pour assurer le guidage de l'aube.1. Mounting device with improved angular positioning of hammer foot blades in a compressor or turbine rotor the rim (5) of the rotor disc comprising a circumferential groove (9) opening on the circumference of the disc in a groove (11 ) of reduced width, groove in which blades are maintained comprising a blade (6) fixed on a rectangular platform (7) extended by a stilt (10) at the end of which is fixed, according to the longitudinal plane of symmetry from the platform, a bulbous foot (8) of reduced circumferential width capable of cooperating with the groove (9), characterized in that the stilt (10) of the blade extends over the entire circumferential width of the blade and cooperates with the groove (11) of the rim of the disc to guide the blade. 2. Dispositif selon la revendication 1, caractérisé en ce que l'échasse (10) de l'aube a une hauteur radiale constante et le guidage est assuré sur toute cette longueur.2. Device according to claim 1, characterized in that the stilt (10) of the blade has a constant radial height and the guidance is provided over this entire length. 3. Dispositif selon l'une des revendications 1 ou 2 caractérisé en ce que des évidements (12) sont réalisés dans l'échasse de l'aube entre le bulbe (8) de celle-ci et chaque extrémité (110) de l'échasse.3. Device according to one of claims 1 or 2 characterized in that recesses (12) are made in the stilt of the blade between the bulb (8) thereof and each end (110) of the stilt.
EP90400670A 1989-03-15 1990-03-14 Blades with hammer-type feet for improved angular positioning Expired - Lifetime EP0388286B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8903374A FR2644524A1 (en) 1989-03-15 1989-03-15 AUBES WITH FOOT HAMMER WITH IMPROVED ANGULAR POSITIONING
FR8903374 1989-03-15

Publications (2)

Publication Number Publication Date
EP0388286A1 true EP0388286A1 (en) 1990-09-19
EP0388286B1 EP0388286B1 (en) 1992-06-03

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EP90400670A Expired - Lifetime EP0388286B1 (en) 1989-03-15 1990-03-14 Blades with hammer-type feet for improved angular positioning

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US (1) US5044886A (en)
EP (1) EP0388286B1 (en)
DE (1) DE69000121T2 (en)
FR (1) FR2644524A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0530097A1 (en) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine motor with angular positioning of the blades
EP2441921A1 (en) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Turbomachine rotor blade roots with adjusting protrusions
EP2075417B1 (en) * 2007-12-27 2016-04-06 Techspace Aero Platform for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5271718A (en) * 1992-08-11 1993-12-21 General Electric Company Lightweight platform blade
GB2313162B (en) * 1996-05-17 2000-02-16 Rolls Royce Plc Bladed rotor
US6736602B2 (en) * 2002-07-31 2004-05-18 United Technologies Corporation Hollow fan hub under blade bumper
FR2856728B1 (en) * 2003-06-27 2005-10-28 Snecma Moteurs TURBOREACTOR COMPRESSOR BLADE
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
JP6434780B2 (en) * 2014-11-12 2018-12-05 三菱日立パワーシステムズ株式会社 Rotor assembly for turbine, turbine, and moving blade

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB137379A (en) * 1919-01-16 1920-01-15 Vickers Ltd Improvements relating to turbine blades
US2295012A (en) * 1941-03-08 1942-09-08 Westinghouse Electric & Mfg Co Turbine blading
FR1192696A (en) * 1957-03-05 1959-10-28 Oerlikon Maschf Axial turbomachine
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
EP0081436A1 (en) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Compressor or turbine rotor, the wheel of which supports the hammer-type foot blades and method of assembling such a rotor
GB2119026A (en) * 1981-03-25 1983-11-09 Rolls Royce Aerofoil blade mounting
FR2616480A1 (en) * 1987-06-10 1988-12-16 Snecma DEVICE FOR LOCKING AUBES WITH FOOT HAMMER ON A TURBOMACHINE DISC AND METHODS OF MOUNTING AND DISASSEMBLING

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4464096A (en) * 1979-11-01 1984-08-07 United Technologies Corporation Self-actuating rotor seal
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB137379A (en) * 1919-01-16 1920-01-15 Vickers Ltd Improvements relating to turbine blades
US2295012A (en) * 1941-03-08 1942-09-08 Westinghouse Electric & Mfg Co Turbine blading
FR1192696A (en) * 1957-03-05 1959-10-28 Oerlikon Maschf Axial turbomachine
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
GB2119026A (en) * 1981-03-25 1983-11-09 Rolls Royce Aerofoil blade mounting
EP0081436A1 (en) * 1981-12-09 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Compressor or turbine rotor, the wheel of which supports the hammer-type foot blades and method of assembling such a rotor
FR2616480A1 (en) * 1987-06-10 1988-12-16 Snecma DEVICE FOR LOCKING AUBES WITH FOOT HAMMER ON A TURBOMACHINE DISC AND METHODS OF MOUNTING AND DISASSEMBLING

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0530097A1 (en) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine motor with angular positioning of the blades
FR2680828A1 (en) * 1991-08-28 1993-03-05 Sev Motorola TURBOMACHINE ROTOR WITH IMPROVED ANGULAR POSITIONING OF AUBES.
EP2075417B1 (en) * 2007-12-27 2016-04-06 Techspace Aero Platform for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel
EP2441921A1 (en) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Turbomachine rotor blade roots with adjusting protrusions
WO2012048957A1 (en) * 2010-10-12 2012-04-19 Siemens Aktiengesellschaft Turbomachine rotor with blade roots with adjusting protrusions
US9664054B2 (en) 2010-10-12 2017-05-30 Siemens Aktiengesellschaft Turbomachine rotor with blade roots with adjusting protrusions

Also Published As

Publication number Publication date
DE69000121D1 (en) 1992-07-09
US5044886A (en) 1991-09-03
FR2644524A1 (en) 1990-09-21
EP0388286B1 (en) 1992-06-03
DE69000121T2 (en) 1993-01-14

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