EP0396726A1 - Segment for locking and sealing a set of vanes mounted on a turbo-engine rotary disk. - Google Patents

Segment for locking and sealing a set of vanes mounted on a turbo-engine rotary disk.

Info

Publication number
EP0396726A1
EP0396726A1 EP89913063A EP89913063A EP0396726A1 EP 0396726 A1 EP0396726 A1 EP 0396726A1 EP 89913063 A EP89913063 A EP 89913063A EP 89913063 A EP89913063 A EP 89913063A EP 0396726 A1 EP0396726 A1 EP 0396726A1
Authority
EP
European Patent Office
Prior art keywords
segment
disc
blades
downstream
turbomachine rotor
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
EP89913063A
Other languages
German (de)
French (fr)
Other versions
EP0396726B1 (en
Inventor
Philippe Patrick Catte
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 EP0396726A1 publication Critical patent/EP0396726A1/en
Application granted granted Critical
Publication of EP0396726B1 publication Critical patent/EP0396726B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/3007—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 turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
  • a first problem consists in ensuring the axial locking of each of the blades in the simplest possible way but also as safe as possible. so that easy disassembly of a blade or the entire stage is also simplified.
  • the second problem is that of the seal between the upstream and downstream of a disc and arises crucially in the compressors of turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
  • the blade roots comprising means for wedging the blades on the upstream face ⁇ of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery
  • the rotor of which comprises an axial locking means downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the disc cavities
  • said downstream locking means of the vanes on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the vanes and the circular groove of the disc, the sum of the thicknesses of the first and second segments being equal to the thickness of the grooves of the blade spoilers.
  • turbomachinery of the type currently studied for example fast propeller turbojet engines whose compressor rotors have very small diameters, it is necessary to minimize the height under the platforms and to gain mass on the compressor blades, the solution above mentioned cannot be used because it is too bulky.
  • the object of the present invention is therefore to replace the anterior double segmentation with a single monobloc segment. performing both locking and sealing functions.
  • the subject of the invention is therefore a turbomachine rotor of the type already indicated above and which is characterized in that the locking means consists of a single split segment with Y-shaped section of which a radially external upstream branch is inserted. in the grooves of the spoilers downstream of the blades and of the disc, the downstream radially external branch of the segment being pressed against the downstream part of the spoilers of the blades.
  • FIG. 1 shows a turbomachine rotor stage fitted with the locking means according to the invention according to a first variant;
  • - Figure 2 shows a second alternative embodiment of the locking segment;
  • FIG. 3 shows a third alternative embodiment of said segment.
  • the rotor disc 1 comprises substantially axial cells 2 into which are inserted the feet 3 of blades 4 having an upstream wedging means 5 on the upstream face of the disc 1 and a downstream spoiler 6 comprising a transverse groove 7 radially oriented towards the axis of the disc.
  • the latter comprises opposite the groove 7 of the blades a groove 8 radially oriented towards its periphery, which will be used for mounting / dismounting the segment.
  • split segment 9 is inserted, the section of which has the shape of a Y with asymmetrical branches 9a and 9b joined together by their common pie 9c.
  • the upstream flat branch 9a is inserted into the groove 7.
  • the downstream branch 9b longer than the branch 9a, has a curved shape which matches the downstream shape of the spoiler 6 and which rises under the platform 10 of the blade.
  • the two branches 9a and 9b can be produced during manufacture with a slight tightening so that during assembly of the segment in its location the downstream branch is pressed against the downstream face of the spoiler 6.
  • the pressure coming from the __ P between the upstream and downstream of the disc combined with the centrifugal force, increases the plating of the downstream branch against the blade.
  • the segment is produced by welding radially internal parts of two annular sheets of which the downstream one has a curved shape and the upstream one is flat.
  • the segment is produced by folding and forming a single annular sheet, the fold of which forms the foot 9c of the Y section of the segment.
  • the segment is produced by machining around a one-piece annular blank.
  • the segment is assembled by placing the foot 9c of the segment in the groove 8c and compressing it radially so that the upstream branch 9a passes under the spoiler 6. Once pressed forward, the segment can be released radially so that the upstream branch 9a enters the groove 7. In operation, the centrifugal force will maintain the segment in la.gorge 7.

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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

Selon l'invention le moyen de verrouillage des pieds (3) d'aubes dans les alvéoles (2) du disque est constitué d'un segment fendu unique (9) à section en forme de Y dont une branche amont radialement externe (9a) est insérée dans la gorge (7) des becquets aval (6) des aubes et du disque (1), la branche aval radialement externe (9b) du segment (9) étant plaquée contre la partie aval des becquets (6) des aubes. Application à des rotors de petit diamètre.According to the invention, the means for locking the blade roots (3) in the cells (2) of the disc consists of a single split segment (9) with a Y-shaped section, including a radially external upstream branch (9a). is inserted into the groove (7) of the downstream spoilers (6) of the vanes and of the disc (1), the radially outer downstream branch (9b) of the segment (9) being pressed against the downstream part of the spoilers (6) of the vanes. Application to small diameter rotors.

Description

SEGMENT D'ARRET ET D'ETANCHEITE D'UN ENSEMBLE D'AUBES MONTE SUR UN DISQUE DE ROTOR DE TURBOMACHINE. STOP AND SEALING SEGMENT OF A SET OF BLADES MOUNTED ON A TURBOMACHINE ROTOR DISC.
La présente invention concerne les rotors de turbomachine et plus particulièrement les moyens de verrouillage axial d'aubes montées dans des brochages axiaux de la périphérie du disque.The present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
Lorsque les aubes de rotors des turbomachines sont fixées dans des brochages axiaux, c'est-à-dire parallèles à l'axe de la turbomachine ou faiblement écartés d'une parallèle a l'axe de la turbomachine, deux problèmes se posent au montage.When the rotor blades of turbomachinery are fixed in axial pinouts, that is to say parallel to the axis of the turbomachine or slightly spaced from a parallel to the axis of the turbomachine, two problems arise in mounting. .
Un premier problème consiste à assurer le verrouillage axial de chacune des aubes de la façon la plus simple possible mais aussi la plus sûre possible et de. sorte que le démontage facile d'une aube ou de l'étage entier soit également simplifié.A first problem consists in ensuring the axial locking of each of the blades in the simplest possible way but also as safe as possible. so that easy disassembly of a blade or the entire stage is also simplified.
Le second problème est celui de 1'étanchéité entre l'amont et l'aval d'un disque et se pose de façon cruciale dans les compresseurs de turbomachines. En effet, si les espaces situés entre les fonds d'alvéoles du disque et les pieds d'aubes ne sont pas masqués convenablement, des volumes importants d'air aval peuvent passer sous les pieds d'aubes et recirculer vers l'amont du compresseur, ce qui diminue le taux de compression de celui-ci et fait chuter de façon prohibitive le rendement global de la turbomachine.The second problem is that of the seal between the upstream and downstream of a disc and arises crucially in the compressors of turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
Le document FR-A-2 603 333 au nom de la demanderesse décrit un rotor de turbomachine, notamment pour turbomachine d'aviation comportant au moins un disque portant un ensemble d'aubes dont les pieds sont montés dans des alvéoles brochés sur. la périphérie du disqueDocument FR-A-2 603 333 in the name of the applicant describes a turbomachine rotor, in particular for an aviation turbomachine comprising at least one disc carrying a set of blades, the feet of which are mounted in spindle-shaped cells. the periphery of the disc
FEUILLE DE REMPLACEMENT selon un axe parallèle du faiblement incliné par rapport à une parallèle à -l'axe longitudinal du moteur, les pieds d'aubes comportant un moyen de calage des aubes sur la face amont άu disque et un becquet arrière possédant une gorge transversale radialement orientée vers l'axe du disque tandis que le disque comporte une gorge circulaire radialement orientée vers sa périphérie, dont le rotor comporte un moyen de verrouillage axial aval des aubes sur le disque, assurant simultanément l'étanchéité entre les pieds d'aube et le fond des alvéoles du disque, ledit moyen de verrouillage aval des aubes sur le disque étant constitué par deux segments fendus dont le premier au moins coopère simultanément avec les gorges des becquets des aubes et la gorge circulaire du disque, la somme des épaisseurs des premier et second segments étant égale à l'épaisseur des gorges des becquets d'aubes.REPLACEMENT SHEET along a parallel axis of slightly inclined with respect to a parallel to the longitudinal axis of the motor, the blade roots comprising means for wedging the blades on the upstream face ά of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery, the rotor of which comprises an axial locking means downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the disc cavities, said downstream locking means of the vanes on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the vanes and the circular groove of the disc, the sum of the thicknesses of the first and second segments being equal to the thickness of the grooves of the blade spoilers.
Ce document constitue l'état de la technique à partir duquel l'invention a été réalisée.This document constitutes the state of the art from which the invention was made.
Dans ce dispositif antérieur, il était nécessaire de pratiquer dans les aubes une gorge suffisamment profonde et large pour recevoir les deux segments.In this prior device, it was necessary to make in the blades a groove deep enough and wide to receive the two segments.
Dans les turbomachines du type actuellement étudié, par exemple les turboréacteurs à hélices rapides dont les rotors de compresseurs ont des diamètres très faible, il est nécessaire de minimiser la hauteur sous les plateformes et de gagner de la masse sur les aubes de compresseur, la solution ci-dessus évoquée n'est pas utilisable parce que trop encombrante.In turbomachinery of the type currently studied, for example fast propeller turbojet engines whose compressor rotors have very small diameters, it is necessary to minimize the height under the platforms and to gain mass on the compressor blades, the solution above mentioned cannot be used because it is too bulky.
Aussi la présente invention a pour but de substituer à la double segmentation antérieure un segment unique monobloc réalisant les deux fonctions de verrouillage et d 'étanchéité.The object of the present invention is therefore to replace the anterior double segmentation with a single monobloc segment. performing both locking and sealing functions.
L'invention a donc pour objet un rotor de turbomachine du type déjà indiqué plus haut et qui est caractérisé en ce que le moyen de verrouillage est constitué d'un segment fendu unique à section en forme de Y dont une branche amont radialement externe est insérée dans les gorges des becquets aval des aubes et du disque, la branche aval radialement externe.du segement étant plaquée contre la partie aval des becquets des aubes .The subject of the invention is therefore a turbomachine rotor of the type already indicated above and which is characterized in that the locking means consists of a single split segment with Y-shaped section of which a radially external upstream branch is inserted. in the grooves of the spoilers downstream of the blades and of the disc, the downstream radially external branch of the segment being pressed against the downstream part of the spoilers of the blades.
D'autres caractéristiques seront présentées en regard des planches annexées parmi lesquelles :Other characteristics will be presented with regard to the attached plates, including:
- la figure 1 montre un étage de rotor de turbomachine équipé du moyen de verrouillage selon l'invention selon une première variante ; - la figure 2 montre une seconde variante d'exécution du segment du verrouillage ;- Figure 1 shows a turbomachine rotor stage fitted with the locking means according to the invention according to a first variant; - Figure 2 shows a second alternative embodiment of the locking segment;
- la figure 3 montre une troisième variante d'exécution dudit segment.- Figure 3 shows a third alternative embodiment of said segment.
En se reportant à la figure 1, le disque 1 de rotor comporte des alvéoles sensiblement axiaux 2 dans lesquels sont insérés les pieds 3 d'aubes 4 possédant un moyen de calage amont 5 sur la face amont du disque 1 et un becquet aval 6 comprenant une gorge transversale 7 radialement orientée vers l'axe du disque. Ce dernier comporte en regard de la gorge 7 des aubes une gorge 8 radialement orientée vers sa périphérie, qui servira au montage/démontage du segment.Referring to Figure 1, the rotor disc 1 comprises substantially axial cells 2 into which are inserted the feet 3 of blades 4 having an upstream wedging means 5 on the upstream face of the disc 1 and a downstream spoiler 6 comprising a transverse groove 7 radially oriented towards the axis of the disc. The latter comprises opposite the groove 7 of the blades a groove 8 radially oriented towards its periphery, which will be used for mounting / dismounting the segment.
Dans la gorge 7 est inséré un segment fendu 9 dont, la section a la forme d'un Y à branches assymétriques 9a et 9b réunies par leur pie àd commun 9c. La branche amont 9a plate est insérée dans la gorge 7.In the groove 7 a split segment 9 is inserted, the section of which has the shape of a Y with asymmetrical branches 9a and 9b joined together by their common pie 9c. The upstream flat branch 9a is inserted into the groove 7.
La branche aval 9b, plus longue que la branche 9a a une forme recourbée qui épouse la forme aval du becquet 6 et qui remonte sous la plateforme 10 de l'aube.The downstream branch 9b, longer than the branch 9a, has a curved shape which matches the downstream shape of the spoiler 6 and which rises under the platform 10 of the blade.
Les deux branches 9a et 9b peuvent être réalisées en fabrication avec un léger serrage de telle sorte que lors du montage du segment dans son emplacement la branche aval soit plaquée contre la face aval du becquet 6. En outre, en fonctionnement la pression provenant du __ P entre l'amont et l'aval du disque, conjuguée à la force centrifuge, augmente le placage de la branche aval contre 1 'aube.The two branches 9a and 9b can be produced during manufacture with a slight tightening so that during assembly of the segment in its location the downstream branch is pressed against the downstream face of the spoiler 6. In addition, in operation the pressure coming from the __ P between the upstream and downstream of the disc, combined with the centrifugal force, increases the plating of the downstream branch against the blade.
Dans la variante montrée à la figure 1, le segment est réalisé par soudage de parties radialement internes de deux tôles annulaires dont celle aval a une forme incurvée et celle amont est plate.In the variant shown in FIG. 1, the segment is produced by welding radially internal parts of two annular sheets of which the downstream one has a curved shape and the upstream one is flat.
Dans la variante d'exécution montrée à la figure 2, le segment est réalisé par pliage et formage d'une tôle annulaire unique dont le pli forme le pied 9c de la section en Y du segment.In the variant shown in FIG. 2, the segment is produced by folding and forming a single annular sheet, the fold of which forms the foot 9c of the Y section of the segment.
Dans la variante d'exécution de la figure 3 le segment est réalisé par usinage autour d'une ébauche annulaire monobloc.In the alternative embodiment of FIG. 3, the segment is produced by machining around a one-piece annular blank.
Si l'on compare cette solution avec celle du document FR-A-2 603 333 précité, on peut constater que dans ce document les aubes devraient comporter une gorge large pour recevoir deux segments alors que dans la présente ' - <ç invention, la fonction d'etancheite ayant été reportée sur la branche aval du segment, la gorge nécessaire dans les pieds d'aubes ne nécessite qu'une largeur minimale.If we compare this solution with that of the document FR-A-2 603 333 cited above, we can see that in this document the blades should have a wide groove to receive two segments whereas in the present ' - < ç invention, the sealing function having been transferred to the downstream branch of the segment, the necessary groove in the blade roots requires only a minimum width.
Ainsi, on peut réaliser les deux fonctions d'etancheite et de verrouillage axial des aubes sur le disque aussi bien que par le passé tout en économisant de la matière et de l'espace sur les aubes.Thus, we can achieve the two functions of sealing and axial locking of the blades on the disc as well as in the past while saving material and space on the blades.
Le montage du segment s'effectue en mettant en place dans la gorge 8 le pied 9c du segment et en comprimant celui-ci radialement de telle sorte que la branche amont 9a passe sous le becquet 6. Une fois plaquée vers l'avant, le segment peut être relâché radialement de sorte que la branche amont 9a pénètre dans la gorge 7. En fonctionnement, la force centrifuge maintiendra le segment dans la.gorge 7.The segment is assembled by placing the foot 9c of the segment in the groove 8c and compressing it radially so that the upstream branch 9a passes under the spoiler 6. Once pressed forward, the segment can be released radially so that the upstream branch 9a enters the groove 7. In operation, the centrifugal force will maintain the segment in la.gorge 7.
L'avantage ainsi procuré permet de diminuer les dimensions des rotors de turbomachines, ou si l'on regarde le problème différemment, d'utiliser un verrouillage efficace par segment fendu sur des rotors de diamètre plus petit. The advantage thus obtained makes it possible to reduce the dimensions of the turbomachine rotors, or if we look at the problem differently, to use effective locking by split segment on rotors of smaller diameter.

Claims

REVENDICATIONS
1. Rotor de turbomachine, notamment pour turbomachine d'aviation comportant au moins un disque portant un ensemble d'aubes dont les pieds sont montés dans des alvéoles brochés sur la périphérie du disque selon un axe parallèle ou faiblement incliné par rapport à une parallèle à l'axe longitudinal du moteur, les pieds (3) d'aubes comportant un moyen de calage (5) des aubes sur la face amont du disque (1) et un becquet aval (6) possédant une gorge transversale (7) radialement orientée vers l'axe du disque, gorge dans laquelle est inséré un moyen de verrouillage axial aval des aubes sur le disque assurant simultanément l'étanchéité entre les pieds (7) d'aube et le fond des alvéoles (2) du disque, tandis que le disque comporte une gorge circulaire (8) radialement orientée vers sa périphérie, caractérisé en ce que le moyen de verrouillage est constitué d'un segment fendu unique (9) à section en forme de Y dont une branche amont radialement externe (9a) est insérée dans la gorge (7) des becquets aval (6) des aubes et du disque (1), la branche aval radialement externe (9b) du segment (9) étant plaquée contre la partie aval des becquets (6) des aubes.1. Turbomachine rotor, in particular for an aviation turbomachine comprising at least one disc carrying a set of blades, the feet of which are mounted in spindle cells on the periphery of the disc along an axis parallel or slightly inclined with respect to a parallel to the longitudinal axis of the engine, the feet (3) of blades comprising a means of wedging (5) of the blades on the upstream face of the disc (1) and a downstream spoiler (6) having a transverse groove (7) radially oriented towards the axis of the disc, groove in which is inserted an axial locking means downstream of the blades on the disc simultaneously ensuring sealing between the feet (7) of the blade and the bottom of the cells (2) of the disc, while the disc has a circular groove (8) radially oriented towards its periphery, characterized in that the locking means consists of a single split segment (9) with a Y-shaped section of which a radially external upstream branch (9a) is inserted e in the groove (7) of the downstream spoilers (6) of the blades and of the disc (1), the radially external downstream branch (9b) of the segment (9) being pressed against the downstream part of the spoilers (6) of the blades.
2. Rotor de turbomachine selon la revendication 1, caractérisé en ce que la branche aval (9b) du segment a une forme incurvée correspondant à la forme de la partie aval des becquets (6) d'aubes.2. Turbomachine rotor according to claim 1, characterized in that the downstream branch (9b) of the segment has a curved shape corresponding to the shape of the downstream part of the spoilers (6) of blades.
3. Rotor de turbomachine selon 1 'une quelconque des revendications 1 ou 2 caractérisé en ce que la branche aval (9b) du segment est plus longue que la branche amont (9a) et remonte radialement sous la plateforme (10) des aubes. 3. Turbomachine rotor according to any one of claims 1 or 2 characterized in that the downstream branch (9b) of the segment is longer than the upstream branch (9a) and rises radially under the platform (10) of the blades.
4. Rotor de turbomachine selon l'une quelconque des revendications 1 à 3 caractérisé en ce que le segment est réalisé avec un léger serrage de ses branches radialement externes (9a, 9b) pour assurer un verrouillage serré des aubes sur le disque et une étanchéité améliorée.4. Turbomachine rotor according to any one of claims 1 to 3 characterized in that the segment is produced with a slight tightening of its radially external branches (9a, 9b) to ensure a tight locking of the blades on the disc and a seal improved.
5. Rotor de turbomachine selon l'une quelconque des revendications 1 à 4 caractérisé en ce que le segment (9) est réalisé par pliage et formage d'une tôle annulaire.5. Turbomachine rotor according to any one of claims 1 to 4 characterized in that the segment (9) is produced by folding and forming an annular sheet.
6. Rotor de turbomachine selon l'une quelconque des revendications 1 à 4 caractérisé en ce que le segment (9) est réalisé par soudage des parties radialement internes de deux tôles annulaires.6. Turbomachine rotor according to any one of claims 1 to 4 characterized in that the segment (9) is produced by welding the radially internal parts of two annular sheets.
7. Rotor de turbomachine selon l'une quelconque des revendications 1 à 4 caractérisé en ce que le segment (9) est réalisé par usinage monobloc d'une ébauche annulaire. 7. Turbomachine rotor according to any one of claims 1 to 4 characterized in that the segment (9) is produced by one-piece machining of an annular blank.
EP89913063A 1988-11-17 1989-11-16 Segment for locking and sealing a set of vanes mounted on a turbo-engine rotary disk Expired - Lifetime EP0396726B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8814913 1988-11-17
FR8814913A FR2639063A1 (en) 1988-11-17 1988-11-17 STOP AND SEGMENT SEGMENT OF A SET OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK

Publications (2)

Publication Number Publication Date
EP0396726A1 true EP0396726A1 (en) 1990-11-14
EP0396726B1 EP0396726B1 (en) 1992-05-13

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EP89913063A Expired - Lifetime EP0396726B1 (en) 1988-11-17 1989-11-16 Segment for locking and sealing a set of vanes mounted on a turbo-engine rotary disk

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US (1) US5052893A (en)
EP (1) EP0396726B1 (en)
FR (1) FR2639063A1 (en)
WO (1) WO1990005837A1 (en)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
FR2694046B1 (en) * 1992-07-22 1994-09-23 Snecma Sealing and retention device for a rotor notched with pinouts receiving blade roots.
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
FR2715975B1 (en) * 1994-02-10 1996-03-29 Snecma Turbomachine rotor with axial or inclined through blade grooves.
JP2726895B2 (en) * 1994-09-14 1998-03-11 川崎重工業株式会社 Mounting structure of ceramic blade
GB2311826B (en) * 1996-04-02 2000-05-10 Europ Gas Turbines Ltd Turbomachines
CZ20002685A3 (en) * 1999-12-20 2001-08-15 General Electric Company Retention system and method for the blades of a rotary machine
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7238008B2 (en) * 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
JP4873200B2 (en) * 2007-03-27 2012-02-08 株式会社Ｉｈｉ Fan rotor blade support structure and turbofan engine having the same
US8038405B2 (en) * 2008-07-08 2011-10-18 General Electric Company Spring seal for turbine dovetail
US8210820B2 (en) * 2008-07-08 2012-07-03 General Electric Company Gas assisted turbine seal
US8011894B2 (en) * 2008-07-08 2011-09-06 General Electric Company Sealing mechanism with pivot plate and rope seal
US8215914B2 (en) * 2008-07-08 2012-07-10 General Electric Company Compliant seal for rotor slot
US8210823B2 (en) * 2008-07-08 2012-07-03 General Electric Company Method and apparatus for creating seal slots for turbine components
US8210821B2 (en) * 2008-07-08 2012-07-03 General Electric Company Labyrinth seal for turbine dovetail
FR2939832B1 (en) * 2008-12-11 2011-01-07 Turbomeca TURBINE WHEEL EQUIPPED WITH AXIAL HOLDING DEVICE LOCKING BLADES WITH RESPECT TO A DISK.
US8657580B2 (en) * 2010-06-17 2014-02-25 Pratt & Whitney Blade retainment system
FR2974863B1 (en) * 2011-05-06 2015-10-23 Snecma TURBOMACHINE BLOWER DISK
FR3127255A1 (en) * 2021-09-23 2023-03-24 Safran Aircraft Engines Rotary assembly for turbomachine
EP4230843A1 (en) * 2022-02-17 2023-08-23 Siemens Energy Global GmbH & Co. KG A rotor arrangement for a rotor of a gas turbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB802476A (en) * 1955-09-29 1958-10-08 Rolls Royce Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines
DE1116094B (en) * 1959-07-22 1961-10-26 Buessing Nutzkraftwagen G M B Floating device for land vehicles
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
FR2324873A1 (en) * 1975-09-17 1977-04-15 Snecma Axial flow turbomachinery rotor - has turbine blade fixing ring which also acts as stage seal
FR2419389A1 (en) * 1978-03-08 1979-10-05 Snecma IMPROVEMENTS TO TURBOMACHINE ROTOR FLANGES
JPS6339741A (en) * 1986-07-30 1988-02-20 Mazda Motor Corp Parts mounting device
FR2603333B1 (en) * 1986-09-03 1990-07-20 Snecma TURBOMACHINE ROTOR COMPRISING A MEANS OF AXIAL LOCKING AND SEALING OF BLADES MOUNTED IN AXIAL PINS OF THE DISC AND MOUNTING METHOD

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9005837A1 *

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FR2639063A1 (en) 1990-05-18
EP0396726B1 (en) 1992-05-13
WO1990005837A1 (en) 1990-05-31
US5052893A (en) 1991-10-01

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