EP0370899B1 - Turbine-bladed rotor disc - Google Patents

Turbine-bladed rotor disc Download PDF

Info

Publication number
EP0370899B1
EP0370899B1 EP89403217A EP89403217A EP0370899B1 EP 0370899 B1 EP0370899 B1 EP 0370899B1 EP 89403217 A EP89403217 A EP 89403217A EP 89403217 A EP89403217 A EP 89403217A EP 0370899 B1 EP0370899 B1 EP 0370899B1
Authority
EP
European Patent Office
Prior art keywords
disc
platform
foot
plate
bladed 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.)
Expired - Lifetime
Application number
EP89403217A
Other languages
German (de)
French (fr)
Other versions
EP0370899A1 (en
Inventor
François Marie Paul Marlin
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0370899A1 publication Critical patent/EP0370899A1/en
Application granted granted Critical
Publication of EP0370899B1 publication Critical patent/EP0370899B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the present invention relates to a finned disc equipped with blades and separate platforms, intended in particular for a turbojet fan or for an aircraft engine compression stage.
  • GB-A- 2 171 151 thus describes a rotor comprising quine blades comprising a blade and a foot, separate inter-blade platforms being mounted by a bulbous foot in an intermediate cell housed on the rim of the disc between two cells carrying the blade roots. This method of fixing imposing additional cells on the blade support disc does not however give complete satisfaction for all applications.
  • GB-A-2006883 also describes a rotor comprising, between the blades, separate platforms, each platform comprising a plate delimiting the internal wall of the gas circulation stream and each axial end of which has a fixing hook connected to the disc .
  • the object of the invention described according to the terms of claim 1 is therefore to produce separate inter-blade platforms for turbomachine rotors, associated with improved means of attachment to a disc ensuring retention both in the in the radial direction and in the axial direction while taking into account the weight reduction requirements, the benefit of which is obvious for rotating parts and which is also an important criterion in the aeronautical applications targeted by the invention.
  • a finned turbomachine rotor disc of the type envisaged above, responding to these problems, is characterized in that that each foot for fixing the platform to the disc, cooperates with a cylindrical seat formed on the rim of said disc, at least one of said platform feet being associated with a rider having a C-shaped section and joining said foot with a tooth-shaped element of the disk, a flange of an element adjacent to the rotor and fixed to the disk being in abutment on said jumper so as to ensure axial locking.
  • FIGS. 1 to 4b relate to a turbojet fan and in particular in the case where the mobile rotor stage comprises large-rope blades associated with separate inter-blade platforms.
  • a fan disc 1 has axially oriented grooves, regularly distributed on the rim, at the periphery of the disc and forming cells 2 in which the feet are held of complementary shape to the fan blades 3.
  • Said rim of the disc 1 is extended on its front face, front and rear being defined with respect to the normal direction of gas flow in the turbomachine, by elements forming teeth 4, spaced from the front face 5 of the disc 1.
  • an annular ring 6 for axially locking the blades 3.
  • the front part of the rim of the disc 1 has a cylindrical bearing surface 7. On the rear part of said rim, a cylindrical bearing surface 8 surmounted by is also provided. an annular spoiler 9, thus creating an annular groove 10.
  • the disc 1 is also equipped with platforms 11 separate from the blades 3.
  • said platforms 11 are metallic and are, for example in the case described of an application to a turbojet fan, of a light metal such than titanium or one of its alloys.
  • Each platform 11, arranged between two consecutive blades 3 consists of an upper plate 12 which delimits the internal wall of the gas circulation stream, on the one hand peripherally between the two blades 3 and on the other hand longitudinally where the front edge 13 of the plate 12 is connected with the rear edge 14 of a support 15 of the inlet cone of the blower and the rear edge 16 comprises, for example, a connection groove at the front external edge 17 of a flange intermediate 18 fixed on the rear face 19 of the disc 1, for example by screw 20 at a fixing flange 21.
  • Said plate 12 is supported by legs, on each side, respectively 22 at the front and 23 at the rear, which are terminated by flanges forming fixing feet, respectively 24 at the front and 25 at the rear.
  • a reinforcing rib 26 is disposed under the internal face of the plate 12, in its middle, oriented in the axial direction, between the two legs 22 and 23.
  • Said foot 25 cooperates with said annular groove 10 of the disc 1 and rests on the bearing cylindrical 8 while the foot 24, at the front, rests on the cylindrical surface 7 of the disc 1.
  • a jumper-shaped element 27, arranged vertically so as to have in section a general shape of C keeps said front foot in place 24, the upper branch 28 of the rider cooperating with the upper surface of the foot 24 and the lower branch 29 cooperating with the internal faces of the disc tooth 4 and of the rod 6.
  • a flange 30 of the support 15 of the inlet cone, in support on the jumpers 27, ensures the axial locking of the assembly.
  • Each rider 27 and the disc tooth 4 further comprising respectively a corresponding bore in which is placed a pin 31 for positioning.
  • the method of mounting the platforms 11 which have just been described is as follows.
  • the rear foot 25 of the platform is introduced into the groove 10 of the disc 1 and the front foot 24 is supported on the front cylindrical surface 7 of the disc 1 then the rider 27 is positioned by placing the pin 31 on the tooth 4 disc.
  • the support 15 of the inlet cone is put in place, the flange 30 of its rear part coming to bear on the jumper 27 and finally, a fixing flange 32 of said support 15 is fixed by bolts at 33 on a flange 34 integral with the front of the disc 1.
  • each platform 111 comprises two box-shaped elements, respectively 111a and 111b, having a generally triangular or trapezoidal cross-section and joined along one side, thus constituting a central rib 126.
  • box elements 111a and 111b can be obtained by winding or by stripping of fabrics of composite material and after assembly, they are joined together by a winding or stripping of fabrics also of composite material, creating an outer skin 111c and also constituting an upper plate 112.
  • the platform 111 also comprises on each edge, a reinforcement element, respectively 35 at the front and 36 at the rear and these reinforcements also form the feet of platform mounting, 124 front and 125 rear respectively.
  • FIG. 4b shows the detail of embodiment of the reinforcement 35.
  • the peripheral lateral edges of the platform 111 each receive a seal, respectively 37 and 38 which provide the seal and the connection between the platform 111 and the blade 3 adjacent, on each side.
  • the other elements of the embodiment described with reference to FIGS. 1 and 2 are kept identical, in particular the fixing of the rear foot 125 engaging in the annular groove 10 of the disc 1 and at the front, the fixing of the front foot 124 by means of a jumper 27, axially blocked by the flange 30 of the support 15 of the fan inlet cone.
  • the assembly method previously described with reference to FIGS. 1 and 2 is also kept identical in the variant embodiment according to FIG. 3.
  • the means for fixing the platform can be provided at the rear identical to those which have been described for the front, namely by using jumpers such as 27.

Description

La présente invention concerne un disque aileté équipé d'aubes et de plates-formes séparées, destiné notamment à une soufflante de turboréacteur ou à un étage de compression de moteur aéronautique.The present invention relates to a finned disc equipped with blades and separate platforms, intended in particular for a turbojet fan or for an aircraft engine compression stage.

Dans la réalisation de rotors de turbomachine, notamment du type envisagé ci-dessus, il est connu, par exemple dans le but de permettre un démontage unitaire dans le cas d'aubes à grande corde présentant un vrillage important et/ou de faciliter leur fabrication, notamment les opérations d'usinage, de prévoir une réalisation des aubes en plusieurs parties. GB-A- 2 171 151 décrit ainsi un rotor comportant des aubes quine comprennent qu'une pale et un pied, des plates-formes séparées inter-aubes étant montées par un pied en bulbe dans un alvéole intermédiaire ménage sur la jante du disque entre deux alvéoles portant les pieds d'aubes. Ce mode de fixation imposant des alvéoles supplémentaires sur le disque support des aubes ne donne pas toutefois entière satisfaction pour toutes les applications.In the production of turbomachine rotors, in particular of the type envisaged above, it is known, for example with the aim of allowing unitary disassembly in the case of blades with a large cord having a large twist and / or of facilitating their manufacture , in particular the machining operations, to provide a realization of the blades in several parts. GB-A- 2 171 151 thus describes a rotor comprising quine blades comprising a blade and a foot, separate inter-blade platforms being mounted by a bulbous foot in an intermediate cell housed on the rim of the disc between two cells carrying the blade roots. This method of fixing imposing additional cells on the blade support disc does not however give complete satisfaction for all applications.

GB-A-2006883 décrit également un rotor comportant entre les aubes des plates-formes séparées, chaque plate-forme comportant un plateau délimitant la paroi interne de la veine de circulation des gaz et dont chaque extrémité axiale comporte un crochet de fixation relié au disque. Le but de l'invention décrite selon les termes de la revendication 1 est par conséquent de réaliser des plates-formes inter-aubes séparées pour rotors de turbomachine, associées à des moyens améliorés de fixation sur un disque assurant une rétention à la fois dans le sens radial et dans le sens axial tout en tenant compte des impératifs de réduction de masse dont l'intérêt est évident pour des pièces tournantes et qui est en outre un critère important dans les applications aéronautiques visées par l'invention.GB-A-2006883 also describes a rotor comprising, between the blades, separate platforms, each platform comprising a plate delimiting the internal wall of the gas circulation stream and each axial end of which has a fixing hook connected to the disc . The object of the invention described according to the terms of claim 1 is therefore to produce separate inter-blade platforms for turbomachine rotors, associated with improved means of attachment to a disc ensuring retention both in the in the radial direction and in the axial direction while taking into account the weight reduction requirements, the benefit of which is obvious for rotating parts and which is also an important criterion in the aeronautical applications targeted by the invention.

Un disque aileté de rotor de turbomachine du type envisagé ci-dessus, répondant à ces problèmes est caractérisé en ce que chaque pied de fixation de la plate-forme sur le disque, coopère avec une portée cylindrique ménagée sur la jante dudit disque, l'un au moins desdits pieds de plate-forme étant associé à un cavalier présentant une section en forme de C et solidarisant ledit pied avec un élément en forme de dent du disque, une bride d'un élément voisin du rotor et fixé au disque étant en appui sur ledit cavalier de manière à assurer le verrouillage axial.A finned turbomachine rotor disc of the type envisaged above, responding to these problems, is characterized in that that each foot for fixing the platform to the disc, cooperates with a cylindrical seat formed on the rim of said disc, at least one of said platform feet being associated with a rider having a C-shaped section and joining said foot with a tooth-shaped element of the disk, a flange of an element adjacent to the rotor and fixed to the disk being in abutment on said jumper so as to ensure axial locking.

Plusieurs modes de réalisation sont proposes pour lesquelles des caractéristiques additionnelles sont prévues, le choix s'effectuant en fonction des applications particulières.Several embodiments are proposed for which additional characteristics are provided, the choice being made according to the particular applications.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre des modes de réalisation de l'invention, en référence aux dessins annexés sur lesquels:

  • ― la figure 1 représente, selon une vue en coupe par un plan passant par l'axe de rotation de la turbomachine, un disque aileté de rotor de turbomachine, selon un mode de réalisation de l'invention;
  • ― la figure 2 représente une vue partielle schématique en perspective du disque aileté représenté sur la figure 1;
  • ― la figure 3 représente, selon une vue en coupe analogue à celle de la figure 1, un disque aileté de turbomachine selon une variante de réalisation de l'invention;
  • ― la figure 4a représente, selon une vue schématique en perspective une plate-forme équipant le disque représenté sur la figure 3;
  • ― la figure 4b représente, selon une vue schématique en perspective, un renfort associé à la plate-forme représentée sur la figure 4a.
Other characteristics and advantages of the invention will be better understood on reading the description which follows of embodiments of the invention, with reference to the appended drawings in which:
  • - Figure 1 shows, in a sectional view through a plane passing through the axis of rotation of the turbomachine, a finned disc of the turbomachine rotor, according to one embodiment of the invention;
  • - Figure 2 shows a schematic partial perspective view of the finned disc shown in Figure 1;
  • - Figure 3 shows, in a sectional view similar to that of Figure 1, a finned turbomachine disk according to an alternative embodiment of the invention;
  • - Figure 4a shows, in a schematic perspective view a platform fitted to the disc shown in Figure 3;
  • - Figure 4b shows, in a schematic perspective view, a reinforcement associated with the platform shown in Figure 4a.

L'application de l'invention représentée sur les figures 1 à 4b concerne une soufflante de turboréacteur et notamment dans le cas où l'étage mobile de rotor comporte des aubes à grande corde associées à des plates-formes inter-aubes séparées. Dans le mode de réalisation de l'invention représenté sur les figures 1 et 2, un disque 1 de soufflante comporte des rainures orientées axialement, régulièrement réparties sur la jante, à la périphérie du disque et formant des alvéoles 2 dans lesquels sont maintenus les pieds de forme complémentaire des aubes 3 de soufflante. Ladite jante du disque 1 est prolongée sur sa face avant, avant et arrière étant définis par rapport au sens normal de circulation des gaz dans la turbomachine, par des éléments formant des dents 4, espacés de la face avant 5 du disque 1. Dans l'espace ainsi ménagé est placé un jonc annulaire 6 de verrouillage axial des aubes 3. La partie avant de la jante du disque 1 comporte une portée cylindrique 7. Sur la partie arrière de ladite jante, est ménagée également une portée cylindrique 8 surmontée d'un becquet annulaire 9, créant ainsi une gorge annulaire 10. Le disque 1 est également équipé de plates-formes 11 séparées des aubes 3.The application of the invention shown in FIGS. 1 to 4b relates to a turbojet fan and in particular in the case where the mobile rotor stage comprises large-rope blades associated with separate inter-blade platforms. In the embodiment of the invention shown in Figures 1 and 2, a fan disc 1 has axially oriented grooves, regularly distributed on the rim, at the periphery of the disc and forming cells 2 in which the feet are held of complementary shape to the fan blades 3. Said rim of the disc 1 is extended on its front face, front and rear being defined with respect to the normal direction of gas flow in the turbomachine, by elements forming teeth 4, spaced from the front face 5 of the disc 1. In the space thus provided is placed an annular ring 6 for axially locking the blades 3. The front part of the rim of the disc 1 has a cylindrical bearing surface 7. On the rear part of said rim, a cylindrical bearing surface 8 surmounted by is also provided. an annular spoiler 9, thus creating an annular groove 10. The disc 1 is also equipped with platforms 11 separate from the blades 3.

Selon le mode de réalisation représenté sur les figures 1 et 2, lesdites plates-formes 11 sont métalliques et sont, par exemple dans le cas décrit d'une application à une soufflante de turboréacteur, en un métal léger tel que le titane ou un de ses alliages. Chaque plate-forme 11, disposée entre deux aubes 3 consécutives se compose d'un plateau supérieur 12 qui délimite la paroi interne de la veine de circulation des gaz, d'une part périphériquement entre les deux aubes 3 et d'autre part longitudinalement où le bord avant 13 du plateau 12 se raccorde avec le bord arrière 14 d'un support 15 du cône d'entrée de la soufflante et le bord arrière 16 comporte, par exemple, un soyage de raccordement au bord externe avant 17 d'un flasque intermédiaire 18 fixé sur la face arrière 19 du disque 1, par exemple par vis en 20 au niveau d'une bride de fixation 21. L'étanchéité de la veine est ainsi assurée tant du côté avant que du côté arrière. Ledit plateau 12 est supporté par des jambes, de chaque côté, respectivement 22 à l'avant et 23 à l'arrière, qui sont terminées par des rebords formant des pieds de fixation, respectivement 24 à l'avant et 25 à l'arrière. Une nervure 26 de renfort est disposée sous la face interne du plateau 12, en son milieu, orientée dans le sens axial, entre les deux jambes 22 et 23. Ledit pied 25 coopère avec ladite gorge annulaire 10 du disque 1 et repose sur la portée cylindrique 8 tandis que le pied 24, à l'avant, repose sur la portée cylindrique 7 du disque 1. Un élément en forme de cavalier 27, disposé verticalement de manière à présenter en section une forme générale de C maintient en place ledit pied avant 24, la branche supérieure 28 du cavalier coopérant avec la surface supérieure du pied 24 et la branche inférieure 29 coopérant avec les faces internes de la dent 4 de disque et du jonc 6. Une bride 30 du support 15 de cône d'entrée, en appui sur les cavaliers 27, assure le verrouillage axial de l'ensemble. Chaque cavalier 27 et la dent 4 de disque comportant en outre respectivement un perçage correspondant dans lequel est placé un pion 31 de positionnement.According to the embodiment shown in Figures 1 and 2, said platforms 11 are metallic and are, for example in the case described of an application to a turbojet fan, of a light metal such than titanium or one of its alloys. Each platform 11, arranged between two consecutive blades 3 consists of an upper plate 12 which delimits the internal wall of the gas circulation stream, on the one hand peripherally between the two blades 3 and on the other hand longitudinally where the front edge 13 of the plate 12 is connected with the rear edge 14 of a support 15 of the inlet cone of the blower and the rear edge 16 comprises, for example, a connection groove at the front external edge 17 of a flange intermediate 18 fixed on the rear face 19 of the disc 1, for example by screw 20 at a fixing flange 21. The sealing of the stream is thus ensured both on the front side and on the rear side. Said plate 12 is supported by legs, on each side, respectively 22 at the front and 23 at the rear, which are terminated by flanges forming fixing feet, respectively 24 at the front and 25 at the rear. . A reinforcing rib 26 is disposed under the internal face of the plate 12, in its middle, oriented in the axial direction, between the two legs 22 and 23. Said foot 25 cooperates with said annular groove 10 of the disc 1 and rests on the bearing cylindrical 8 while the foot 24, at the front, rests on the cylindrical surface 7 of the disc 1. A jumper-shaped element 27, arranged vertically so as to have in section a general shape of C keeps said front foot in place 24, the upper branch 28 of the rider cooperating with the upper surface of the foot 24 and the lower branch 29 cooperating with the internal faces of the disc tooth 4 and of the rod 6. A flange 30 of the support 15 of the inlet cone, in support on the jumpers 27, ensures the axial locking of the assembly. Each rider 27 and the disc tooth 4 further comprising respectively a corresponding bore in which is placed a pin 31 for positioning.

Le mode de montage des plates-formes 11 qui viennent d'être décrites est le suivant. Le pied arrière 25 de plate-forme est introduit dans la gorge 10 du disque 1 et le pied avant 24 est mis en appui sur la portée cylindrique avant 7 du disque 1 puis le cavalier 27 est positionné en plaçant le pion 31 sur la dent 4 de disque. Le support 15 du cône d'entrée est mis en place, la bride 30 de sa partie arrière venant en appui sur le cavalier 27 et enfin, une bride de fixation 32 dudit support 15 est fixée par boulons en 33 sur une bride 34 solidaire de la face avant du disque 1.The method of mounting the platforms 11 which have just been described is as follows. The rear foot 25 of the platform is introduced into the groove 10 of the disc 1 and the front foot 24 is supported on the front cylindrical surface 7 of the disc 1 then the rider 27 is positioned by placing the pin 31 on the tooth 4 disc. The support 15 of the inlet cone is put in place, the flange 30 of its rear part coming to bear on the jumper 27 and finally, a fixing flange 32 of said support 15 is fixed by bolts at 33 on a flange 34 integral with the front of the disc 1.

Selon une variante de réalisation de l'invention, représentée sur les figures 3, 4a 4b, pour laquelle la description qui va suivre conserve les mêmes références pour les pièces et éléments identiques à ceux qui ont été décrits en référence aux figures 1 et 2 et donne une référence augmentée d'une centaine pour les pièces ou éléments modifiés, les plates-formes 111 sont constituées en matériau composite. Selon ce mode de réalisation, chaque plate-forme 111 comprend deux éléments en forme de caisson, respectivement 111a et 111b, présentant une section de forme générale triangulaire ou trapézoïdale et accolés suivant un côté, constituant ainsi une nervure centrale 126. Ces éléments en caisson 111a et 111b peuvent être obtenus par bobinage ou par drappage de tissus en matériau composite et après assemblage, ils sont solidarisés par un bobinage ou un drappage de tissus également en matériau composite, créant une peau extérieure 111c et constituant également un plateau supérieur 112.According to an alternative embodiment of the invention, represented in FIGS. 3, 4a 4b, for which the description which follows will retain the same references for the parts and elements identical to those which have been described with reference to FIGS. 1 and 2 and gives a reference increased by a hundred for the modified parts or elements, the platforms 111 are made of composite material. According to this embodiment, each platform 111 comprises two box-shaped elements, respectively 111a and 111b, having a generally triangular or trapezoidal cross-section and joined along one side, thus constituting a central rib 126. These box elements 111a and 111b can be obtained by winding or by stripping of fabrics of composite material and after assembly, they are joined together by a winding or stripping of fabrics also of composite material, creating an outer skin 111c and also constituting an upper plate 112.

La plate-forme 111 comporte également sur chaque bord, un élément de renfort, respectivement 35 à l'avant et 36 à l'arrière et ces renforts forment également les pieds de fixation de la plate-forme, respectivement 124 à l'avant et 125 à l'arrière. La figure 4b montre le détail de réalisation du renfort 35. Les bords latéraux périphériques de la plate-forme 111 reçoivent chacun un joint, respectivement 37 et 38 qui assurent l'étanchéité et le raccordement entre la plate-forme 111 et l'aube 3 adjacente, de chaque côté. Par ailleurs les autres éléments de la réalisation décrite en référence aux figures 1 et 2 sont conservés identiques, notamment la fixation du pied arrière 125 s'engageant dans la gorge annulaire 10 du disque 1 et à l'avant, la fixation du pied avant 124 au moyen d'un cavalier 27, bloqué axialement par la bride 30 du support 15 du cône d'entrée de soufflante. Le mode de montage précédemment décrit en référence aux figures 1 et 2 est également conservé identique dans la variante de réalisation selon la figure 3.The platform 111 also comprises on each edge, a reinforcement element, respectively 35 at the front and 36 at the rear and these reinforcements also form the feet of platform mounting, 124 front and 125 rear respectively. FIG. 4b shows the detail of embodiment of the reinforcement 35. The peripheral lateral edges of the platform 111 each receive a seal, respectively 37 and 38 which provide the seal and the connection between the platform 111 and the blade 3 adjacent, on each side. Furthermore, the other elements of the embodiment described with reference to FIGS. 1 and 2 are kept identical, in particular the fixing of the rear foot 125 engaging in the annular groove 10 of the disc 1 and at the front, the fixing of the front foot 124 by means of a jumper 27, axially blocked by the flange 30 of the support 15 of the fan inlet cone. The assembly method previously described with reference to FIGS. 1 and 2 is also kept identical in the variant embodiment according to FIG. 3.

Une autre variante de réalisation non représentée aux dessins mais qui se déduit directement des représentations données peut être envisagée. Dans certaines applications particulières où il apparaîtrait que le becquet 9 du disque 1 formant la gorge annulaire 10 risque de présenter une fragilité inacceptable, les moyens de fixation de la plate-forme peuvent être prévus à l'arrière identiques à ceux qui ont été décrits pour l'avant, à savoir en utilisant des cavaliers tels que 27.Another alternative embodiment not shown in the drawings but which can be deduced directly from the representations given can be envisaged. In certain particular applications where it would appear that the spoiler 9 of the disc 1 forming the annular groove 10 risks presenting an unacceptable fragility, the means for fixing the platform can be provided at the rear identical to those which have been described for the front, namely by using jumpers such as 27.

Claims (6)

1. Bladed rotor disc for a turboshaft engine composed of a disc (1) fitted with blades (3) constituted solely by a blade and fixing root and by separate platforms, each platform (11; 111) comprising a plate (12; 112) delimiting the inner wall of the gas flow and of which each axial end is connected to an element forming a foot (24, 25; 124, 125) for fixing it to the disc (1), characterised in that each foot (24, 25; 124, 125) works in conjunction respectively with a cylindrical bearing surface (7, 8) formed on the rim of the disc, one at least of the said feet (24; 124) of the platform (11; 111) being associated with a clamping yoke (27) having a cross section in the shape of a C and fastening the said foot (24; 124) to a tooth-shaped element (4) on the disc (1), a flange (30) on an element (15) close to the rotor and fixed to the disc (1) pressing against the said clamping yoke (27) in such a way as to ensure axial locking.
2. Bladed rotor disc of a turboshaft engine in accordance with Claim 1 in which one of the said clamping yokes (27) is associated with the foot (24, 25; 124, 125) of the platform (11; 111) both at the front and the rear.
3. Bladed rotor disc of a turboshaft engine in accordance with Claim 1 in which the said clamping yoke (27) is associated, on the front upper side of the disc (1) with a foot (24; 124) of the platform (11, 111) and on the lower side with a tooth (4) on the disc (1) and to a locking ring (6) placed between the said tooth (4) and the face (5) of the disc (1), and on the rear side, the foot (25; 125) of the platform (11; 111) is placed in an annular slot (10) forming a nib (9) on the rear part of the rim of the disc (1).
4. Bladed rotor disc of a turboshaft engine in accordance with any of the Claims 1 to 3 in which the face of the rim of the disc (1) and the associated clamping yoke (27) comprise respectively a hole to receive a locating peg (31).
5. Bladed rotor disc of a turboshaft engine in accordance with any of Claims 1 to 4 in which the said platforms (11) are made of metal and in each platform the said plate (12) is connected respectively to each foot (24, 25) by a connecting leg (22, 23), a reinforcing rib (26), fixed to the inner surface of the said plate (12) extending from one leg to the other (22, 23) each axial edge (13, 16) of the said plate (12) of the platform (11) working in conjunction with the adjacent edge (14, 17) of the said neighbouring element (15, 18) of the rotor in such a way as to ensure a seal and the continuity of the inner wall of the gas flow.
6. Bladed rotor disc of a turboshaft engine in accordance with any of Claims 1 to 4 in which the said platforms (111) are made of a composite material, each being composed of two elements (111a, 111b) of triangular cross section placed together and fixed together by an outer skin (111c) forming the said plate (112) of the platform (111) and the said fixing feet (124, 125) are constituted at each axial extremity respectively by a reinforcement (35, 36), a seal (37, 38) being placed along each peripheral edge of the plate (112) of the platform (111), ensuring the connection between the platforms (111) and the blades (3).
EP89403217A 1988-11-23 1989-11-22 Turbine-bladed rotor disc Expired - Lifetime EP0370899B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8815234 1988-11-23
FR8815234A FR2639402B1 (en) 1988-11-23 1988-11-23 TURBOMACHINE ROTOR WING DISC

Publications (2)

Publication Number Publication Date
EP0370899A1 EP0370899A1 (en) 1990-05-30
EP0370899B1 true EP0370899B1 (en) 1992-01-02

Family

ID=9372135

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89403217A Expired - Lifetime EP0370899B1 (en) 1988-11-23 1989-11-22 Turbine-bladed rotor disc

Country Status (4)

Country Link
US (1) US5049035A (en)
EP (1) EP0370899B1 (en)
DE (1) DE68900646D1 (en)
FR (1) FR2639402B1 (en)

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2669686B1 (en) * 1990-11-28 1994-09-02 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
FR2679296B1 (en) * 1991-07-17 1993-10-15 Snecma SEPARATE INTER-BLADE PLATFORM FOR TURBOMACHINE ROTOR WING DISC.
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
GB9208409D0 (en) * 1992-04-16 1992-06-03 Rolls Royce Plc Rotors for gas turbine engines
GB9209895D0 (en) * 1992-05-07 1992-06-24 Rolls Royce Plc Rotors for gas turbine engines
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
FR2706528B1 (en) * 1993-06-10 1995-09-01 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
GB0614640D0 (en) * 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
US8568102B2 (en) * 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
FR2960589B1 (en) * 2010-05-28 2014-05-02 Snecma WHEEL A BLADE FOR A TURBOMACHINE, SUCH AS A TURBOJET OR AIRCRAFT TURBOPROPULSER
FR2963383B1 (en) * 2010-07-27 2016-09-09 Snecma DUST OF TURBOMACHINE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE EQUIPPED WITH SUCH A DAWN
FR2965843B1 (en) * 2010-10-06 2012-11-09 Snecma ROTOR FOR TURBOMACHINE
FR2973434A1 (en) * 2011-03-30 2012-10-05 Snecma CMC TURBINE DISPENSER ADAPTED TO THE SUPPORT OF AN INTERNAL METAL TURBINE CASING BY RADIAL CONTACT
FR2974864B1 (en) * 2011-05-04 2016-05-27 Snecma ROTOR OF TURBOMACHINE WITH MEANS OF AXIAL RETENTION OF AUBES
FR2974863B1 (en) * 2011-05-06 2015-10-23 Snecma TURBOMACHINE BLOWER DISK
US8777576B2 (en) * 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
FR2982635B1 (en) * 2011-11-15 2013-11-15 Snecma AUBES WHEEL FOR A TURBOMACHINE
US20160053636A1 (en) * 2013-03-15 2016-02-25 United Technologies Corporation Injection Molded Composite Fan Platform
US9845699B2 (en) * 2013-03-15 2017-12-19 Gkn Aerospace Services Structures Corp. Fan spacer having unitary over molded feature
FR3010442B1 (en) * 2013-09-09 2015-10-09 Snecma REDUCED MONOBLOC DRAWING DISK IN WAVE FOOT, PREFERABLY FOR AIRCRAFT TURBOMACHINE BLOWER
FR3022944B1 (en) * 2014-06-26 2020-02-14 Safran Aircraft Engines ROTARY ASSEMBLY FOR TURBOMACHINE
US10024234B2 (en) * 2014-09-08 2018-07-17 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
FR3035678B1 (en) * 2015-04-29 2017-05-12 Snecma DAWN WITH PLATFORMS HAVING A RESTRAINT LEG
FR3038653B1 (en) * 2015-07-08 2017-08-04 Snecma ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
US9976426B2 (en) * 2015-07-21 2018-05-22 United Technologies Corporation Fan platform with stiffening feature
US10215046B2 (en) * 2015-11-23 2019-02-26 United Technologies Corporation Airfoil platform having dual pin apertures and a vertical stiffener
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
FR3073907B1 (en) * 2017-11-17 2020-12-11 Safran Aircraft Engines RETAINING BODY FOR TURBOMACHINE PLATFORM
US20240125242A1 (en) * 2022-10-14 2024-04-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2873088A (en) * 1953-05-21 1959-02-10 Gen Electric Lightweight rotor construction
BE540433A (en) * 1954-08-12
BE562857A (en) * 1956-11-30
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
GB1232506A (en) * 1969-10-28 1971-05-19
GB1318654A (en) * 1970-12-05 1973-05-31 Secr Defence Bladed rotors
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
GB2006883B (en) * 1977-10-27 1982-02-24 Rolls Royce Fan or compressor stage for a gas turbine engine
US4171930A (en) * 1977-12-28 1979-10-23 General Electric Company U-clip for boltless blade retainer
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines

Also Published As

Publication number Publication date
EP0370899A1 (en) 1990-05-30
DE68900646D1 (en) 1992-02-13
FR2639402B1 (en) 1990-12-28
FR2639402A1 (en) 1990-05-25
US5049035A (en) 1991-09-17

Similar Documents

Publication Publication Date Title
EP0370899B1 (en) Turbine-bladed rotor disc
CA2746979C (en) Turbine wheel with an axial retention system for vanes
CA2824379C (en) Fan rotor and associated turbojet engine
EP2369136B1 (en) Weight-reduced single-piece multi-stage drum of an axial flow compressor
CA2647057C (en) Sectorized distributor for a turbine
EP3074639B1 (en) Fan, in particular for a turbo engine, and flange for said fan
EP3074638A1 (en) Fan for a turbomachine
EP2204541A1 (en) Rotor stage of an integral bladed compressor drum of an axial turbomachine and corresponding manufacturing method.
FR2943984A1 (en) Propeller for turbine engine e.g. open rotor type turbine engine, of aircraft, has hub comprising two annular type portions that are fixed to each other and defining part of recess opening
EP2427659B1 (en) Stator shroud of aircraft turbine engine with slots for relieving mechanical stress on blades
FR2978798A1 (en) Angular sector for rectifier of compressor in turbine of turboshaft engine e.g. turbojet, of aircraft, has hook projecting toward from suction face of blade, and recess receiving thinned part of external ring of sector of adjacent rectifier
FR2990001A1 (en) Intermediate casing for turbojet, has fixing ring for assembling intermediate casing with thrust reverser casing, where fixing ring includes radial annular leg, and heat exchanger is partly fixed to radial annular leg
EP3797224A1 (en) Improved turbmachine fan disc
EP3683450B1 (en) Turbine engine rotor assembly
EP3201438B1 (en) Rotor blade of a turbomachine comprising a flange which abuts a blocking notch of a rotor disc
FR2960589A1 (en) Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles
EP3433469A1 (en) Fan assembly, disk and platform
EP1319842A1 (en) Rotor or rotating element for turbocompressor
FR2954420A1 (en) Outer shell part for rectifier of high pressure compressor in jet engine of aircraft, has reinforcement fixedly arranged on outer surface of core, between two directly consecutive holes, so as to be supported against each of flanges
EP4359650A1 (en) Fan module impeller, and jet turbine engine equipped with such an impeller
FR2587060A1 (en) Device for fastening flanges to a turbine wheel
FR2879265A1 (en) Diffuser for single-celled centrifugal pump of multi-stage pump, has helical blades with projections whose cooperation with notches in flange and/or envelope permits to maintain blades in position between inner flange and outer envelope

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19891204

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19910130

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 68900646

Country of ref document: DE

Date of ref document: 19920213

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20071113

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20071029

Year of fee payment: 19

Ref country code: FR

Payment date: 20071029

Year of fee payment: 19

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20081122

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20090731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090603

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081130