EP2011966A2 - Device for supplying ventilation air to the vanes of a low-pressure turbine of a gas turbine engine - Google Patents

Device for supplying ventilation air to the vanes of a low-pressure turbine of a gas turbine engine Download PDF

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Publication number
EP2011966A2
EP2011966A2 EP08159726A EP08159726A EP2011966A2 EP 2011966 A2 EP2011966 A2 EP 2011966A2 EP 08159726 A EP08159726 A EP 08159726A EP 08159726 A EP08159726 A EP 08159726A EP 2011966 A2 EP2011966 A2 EP 2011966A2
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EP
European Patent Office
Prior art keywords
segments
turbine
drum
rim
blades
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
EP08159726A
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German (de)
French (fr)
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EP2011966A3 (en
EP2011966B1 (en
Inventor
Didier Escure
Jacques Bart
Stéphane Rousselin
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP2011966A2 publication Critical patent/EP2011966A2/en
Publication of EP2011966A3 publication Critical patent/EP2011966A3/en
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    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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 the field of turbomachines. It is aimed at ventilating low pressure turbine blades in a double-body gas turbine engine.
  • turbomachinery it is common to use air taken from the high-pressure compressor, HP, to cool rooms in a warmer environment.
  • HP high-pressure compressor
  • This can be HP turbine blade, disk bores, etc.
  • the low-pressure turbine, BP is part of the ventilated zones: in particular it is made that air comes to cool the blade attachments circulating between the blade root, its attachment and the rim of the disk.
  • the turbine section of a double-body gas turbine engine comprises a stage 2 of HP turbine and a set of LP turbines downstream of a distributor 4 disposed between the stage 2 and the first stage of the LP turbine.
  • the entire LP turbine is composed here of four disks bolted to form a module. Each disc has a ferrule on both sides of its plane. The ferrules of two adjacent discs are bolted together. Rectifiers 5 are interposed between the different stages.
  • the cells 31 are machined peripherally on the rim of the discs in which vanes 6 are slid and axially locked by an axial retention segment 8.
  • the segments have an arcuate shape and are arranged in abutment against a face of the disc rim between a hook 61 and the face 62 of the blade roots to which the hook is attached. They hold the blades against any axial displacement.
  • the segments are scalloped and slid into a peripheral groove 32.
  • the segment is first angularly offset to allow the blade roots to be inserted into their cell and then the segment is angularly displaced so that the peaks of the festooned portion are engaged between the face of the foot and the hook. each dawn. As the segment is retained in the groove, the assembly is immobilized axially.
  • the circulation of the ventilation air represented on the Figures 3 and 4 , which illustrate two different architectures of the prior art, comprises an air flow, illustrated by the arrow F, from the DBP1 distributor upstream of the first LP turbine stage which, for each stage, is guided between the shell V1 of the disc and the VE sealing ring, bypasses the axial retention segments 8 and reaches the fasteners of the turbine blades.
  • a drum is composed of two disks 11 and 12 connected by a shell 13 on which are formed the sealing elements 13E.
  • a ferrule 14 is secured to the downstream disc 12 and includes orifices 14A for the passage of fastening means, bolts not shown in the figure, to another group or adjacent disc.
  • ferrules for the sealing elements are not necessary since they are integrated with the drum.
  • the disks also have the same structure as in previous achievements and the assembly of the blades of the second stage of the group of this figure is also the same.
  • the applicant has set a goal to find a solution that would allow in the case of drum disks to perform the ventilation of the fasteners and the axial retention of the blades.
  • a ventilation air supply device in a turbine rotor of a gas turbine engine comprising a first and a second turbine disc and a ferrule downstream of the second disc together forming a one-piece drum, the second turbine disk comprising cells for housing the turbine blades, and the vanes being axially retained by axial retaining segments.
  • the device is characterized in that at least one hole is made in said ferrule placing the inside of the drum in communication with at least a portion of the cells by a passage through the segments.
  • the axial retaining segments comprise an annular channel open laterally on said bore and on the cells.
  • the segments comprise radial channels made in particular not machining.
  • the monobloc drum 10 comprises the discs 11 and 12 connected by a ferrule 13 and with a rear ferrule 14.
  • the elements are monoblock in that they are either machined to form a drum in one piece, or welded together.
  • the rim 12J of the disc 12 has axial recesses in which the feet 6P of the vanes 6 are slid axially. To wedge them axially, the blades comprise a hook 6B downstream of the rear transverse face 6A of the foot 6P.
  • a 12P bore is provided in the downstream wall of the disk rim 12J through the downstream ferrule 14. This drilling is radial, it puts in communication the internal drum volume and the bottom of a groove 12R '. This groove is open radially. It is formed between the rim 12J and a transverse flange parallel to the rim 12J.
  • the axial retention segments 18 are housed in this groove 12R '. These arcuate segments extend radially along the downstream face of the rim and mask the downstream faces 6A of the blade feet 6P. The segments are slid between the downstream face 6A 6P feet and their corresponding downstream hook. They block the feet of dawn in this way against any axial displacement.
  • the base 18B of the segments is thick and occupies in width the groove 12R '.
  • an annular channel 18C is machined in the thickness of the base 18B. This channel communicates the holes 12P with the bottom of the cells and thus forms a radial passage 18P and axial.
  • the air flows from the upstream zone of the turbine rotor. It passes through the stator 20 through a passage 20P and is divided into several streams.
  • the flow F1 is guided towards the passage formed between the shell and a flange for attaching the ferrule to the first disk 11 to ventilate the cells of the disk 11.
  • Another portion F2 of the flow passes between the central openings of two disks 11 and 12 , and the stator 20, goes up along the downstream face of the disk 12 and engages in the holes 12P.
  • the holes communicating with the bottom of the groove in line with the channel 18C, the air is found in the annular channel 18C where it is distributed in the existing spaces between the blade roots and the bottom of the cells. Leaving this space, the air is then guided into the gas vein.
  • the cost in mass is low or non-existent on the thickness of the base 18B.
  • the segment performs its function of axial retention without loss of efficiency.
  • This segment 18 ' instead of a continuous channel formed in the base 18'B, comprises a plurality of blind 18'C blinds machined in the mass of the base 18'B. These radial lunulas communicate on one side with the holes 12P and are open axially on the side of the face bearing against the rim 12J at the cell bottom. They form the passages 18'P. The ventilation of the blades of the blades is provided in the same way as before. The air from the upstream turbine distributor circulates inside the drum; part of this flow is driven through the holes 12P and is guided by the axial retention segments in the free spaces between the cell bottoms and the blade roots.

Abstract

The device has a monoblock drum including turbine discs (11, 12), where a rim (12J) of the disc (12) includes slots in which feet (6P) of blades (6) of a turbine of a gas turbine engine are slid in axial manner. The blades are axially retained by axial retaining segments (18). A hole (12P) is formed in a rear shell (14) below the rim that is in communication at inner side of a monoblock drum with the slots of the disc (12). A passage is formed in the segments. The segments include a base housed in a groove formed in the drum.

Description

La présente invention concerne le domaine des turbomachines. Elle vise la ventilation des aubes de turbine basse pression dans un moteur à turbine à gaz à double corps.The present invention relates to the field of turbomachines. It is aimed at ventilating low pressure turbine blades in a double-body gas turbine engine.

Dans les turbomachines il est courant d'utiliser de l'air prélevé sur le compresseur à haute pression, HP, pour refroidir des pièces situées en environnement plus chaud. Il peut s'agir de l'aube de turbine HP, des alésages des disques, etc.In turbomachinery it is common to use air taken from the high-pressure compressor, HP, to cool rooms in a warmer environment. This can be HP turbine blade, disk bores, etc.

La turbine à basse pression, BP, fait partie des zones ventilées : en particulier il est fait en sorte que de l'air vienne refroidir les attaches des aubes en circulant entre le pied d'aube, son attache et la jante du disque.The low-pressure turbine, BP, is part of the ventilated zones: in particular it is made that air comes to cool the blade attachments circulating between the blade root, its attachment and the rim of the disk.

On a représenté sur la figure 1, la section de turbine d'un moteur à turbine à gaz à double corps. Cette section comprend un étage 2 de turbine HP et un ensemble de turbines BP en aval d'un distributeur 4 disposé entre l'étage 2 et le premier étage de la turbine BP. L'ensemble de la turbine BP est composé ici de quatre disques boulonnés de manière à constituer un module. Chaque disque comporte une virole de part et d'autre de son plan. Les viroles de deux disques adjacents sont fixées par boulonnage entre elles. Des redresseurs 5 sont intercalés entre les différents étages.We have shown on the figure 1 , the turbine section of a double-body gas turbine engine. This section comprises a stage 2 of HP turbine and a set of LP turbines downstream of a distributor 4 disposed between the stage 2 and the first stage of the LP turbine. The entire LP turbine is composed here of four disks bolted to form a module. Each disc has a ferrule on both sides of its plane. The ferrules of two adjacent discs are bolted together. Rectifiers 5 are interposed between the different stages.

On a représenté sur la figure 2 le mode d'attache des aubes sur les disques 3 de turbine BP. Des alvéoles 31 sont usinées à la périphérie sur la jante des disques dans lesquelles des aubes 6 sont glissées et bloquées axialement par un segment 8 de rétention axiale. Les segments ont une forme en arc de cercle et sont disposés en appui contre une face de la jante du disque entre un crochet 61 et la face 62 des pieds des aubes à laquelle le crochet est attaché. Ils retiennent les aubes contre tout déplacement axial. Les segments sont festonnés et sont glissés dans une rainure 32 périphérique. Comme on le voit, le segment est d'abord décalé angulairement pour permettre l'introduction du pied des aubes dans leur alvéole puis le segment est déplacé angulairement de façon que les sommets de la partie festonnée soient engagés entre la face du pied et le crochet de chaque aube. Comme le segment est retenu dans la rainure, l'ensemble est immobilisé axialement.We have shown on the figure 2 the mode of attachment of the blades on the LP turbine discs 3. The cells 31 are machined peripherally on the rim of the discs in which vanes 6 are slid and axially locked by an axial retention segment 8. The segments have an arcuate shape and are arranged in abutment against a face of the disc rim between a hook 61 and the face 62 of the blade roots to which the hook is attached. They hold the blades against any axial displacement. The segments are scalloped and slid into a peripheral groove 32. As can be seen, the segment is first angularly offset to allow the blade roots to be inserted into their cell and then the segment is angularly displaced so that the peaks of the festooned portion are engaged between the face of the foot and the hook. each dawn. As the segment is retained in the groove, the assembly is immobilized axially.

Par ailleurs, la circulation de l'air de ventilation représentée sur les figures 3 et 4, qui illustrent deux architectures différentes de l'art antérieur, comprend un flux d'air, illustré par la flèche F, issu du distributeur DBP1 en amont du premier étage de turbine BP qui, pour chaque étage, est guidé entre la virole V1 du disque et la virole d'étanchéité VE, contourne les segments 8 de rétention axiale et parvient jusqu'aux attaches des aubes de turbine.Moreover, the circulation of the ventilation air represented on the Figures 3 and 4 , which illustrate two different architectures of the prior art, comprises an air flow, illustrated by the arrow F, from the DBP1 distributor upstream of the first LP turbine stage which, for each stage, is guided between the shell V1 of the disc and the VE sealing ring, bypasses the axial retention segments 8 and reaches the fasteners of the turbine blades.

Dans un contexte de réduction de masse et de simplification de l'architecture de la machine, on est amené à grouper les disques par deux ou plus pour réaliser des tambours en une seule pièce. Les éléments sont soudés entre eux et forment un bloc. Comme on le voit sur la figure 5, un tambour est composé de deux disques 11 et 12 reliés par une virole 13 sur laquelle sont ménagés les éléments d'étanchéité 13E. Une virole 14 est solidaire du disque aval 12 et comprend des orifices 14A pour le passage de moyens d'attache, boulons non représentés sur la figure, à un autre groupe ou disque adjacent. Dans le cas d'une telle structure, des viroles pour les éléments d'étanchéité ne sont pas nécessaires puisqu'ils sont intégrés au tambour. Les disques par ailleurs ont la même structure que dans les réalisations antérieures et le montage des aubes du deuxième étage du groupe de cette figure est aussi le même. Cela signifie pour le disque 12 que les aubes 6 sont logées dans des alvéoles ménagées sur la jante 12J et sont retenues axialement par des segments 8 de rétention glissées à la fois dans une rainure radiale 12R, perpendiculaire à l'axe du rotor 12 et entre la face arrière 62 du pied des aubes et son crochet 61 associé.In a context of mass reduction and simplification of the architecture of the machine, it is necessary to group the discs by two or more to produce drums in one piece. The elements are welded together and form a block. As we see on the figure 5 , a drum is composed of two disks 11 and 12 connected by a shell 13 on which are formed the sealing elements 13E. A ferrule 14 is secured to the downstream disc 12 and includes orifices 14A for the passage of fastening means, bolts not shown in the figure, to another group or adjacent disc. In the case of such a structure, ferrules for the sealing elements are not necessary since they are integrated with the drum. The disks also have the same structure as in previous achievements and the assembly of the blades of the second stage of the group of this figure is also the same. This means for the disk 12 that the blades 6 are housed in cavities formed on the rim 12J and are retained axially by retention segments 8 slid at the same time in a radial groove 12R, perpendicular to the axis of the rotor 12 and between the rear face 62 of the blade root and its associated hook 61.

Pour une solution de ce type, il se pose la question de l'acheminement de l'air de ventilation jusqu'aux attaches des aubes. L'air est prélevé depuis l'intérieur du tambour et doit parvenir jusqu'au niveau du deuxième disque 12 sur le tambour. Le problème ne se pose pas pour le premier disque. La solution qui consisterait à percer la jante 12J du disque 12 au niveau de l'alvéole, pour que l'air parvienne jusqu'aux attaches, comme cela est indiqué en P n'est pas possible en raison des concentrations de contraintes qui seraient engendrés par les perçages.For a solution of this type, there is the question of the routing of the ventilation air to the blades of the blades. The air is taken from the inside of the drum and must reach the level of the second disc 12 on the drum. The problem does not arise for the first disc. The solution that would be to pierce the rim 12J of the disc 12 at the cell, so that the air reaches the fasteners, as indicated in P is not possible because of the stress concentrations that would be generated by the holes.

La demanderesse s'est fixé comme objectif de trouver une solution qui permettrait dans le cas de tambour des disques de réaliser la ventilation des attaches et la rétention axiales des aubes.The applicant has set a goal to find a solution that would allow in the case of drum disks to perform the ventilation of the fasteners and the axial retention of the blades.

Conformément à l'invention, on parvient à cet objectif avec un dispositif d'alimentation en air de ventilation dans un rotor de turbine d'un moteur à turbine à gaz comportant un premier et un deuxième disques de turbine et une virole en aval du deuxième disque formant ensemble un tambour monobloc, le deuxième disque de turbine comprenant des alvéoles pour loger les aubes de turbine, et les aubes étant retenues axialement par des segments de retenue axiale. Le dispositif est caractérisé par le fait qu'au moins un perçage est réalisé dans ladite virole mettant en communication l'intérieur du tambour avec au moins une partie des alvéoles par un passage à travers les segments.According to the invention, this objective is achieved with a ventilation air supply device in a turbine rotor of a gas turbine engine comprising a first and a second turbine disc and a ferrule downstream of the second disc together forming a one-piece drum, the second turbine disk comprising cells for housing the turbine blades, and the vanes being axially retained by axial retaining segments. The device is characterized in that at least one hole is made in said ferrule placing the inside of the drum in communication with at least a portion of the cells by a passage through the segments.

On peut réaliser ce passage de différentes façons. Conformément à un premier mode de réalisation, les segments de retenue axiale comportent un canal annulaire ouvert latéralement sur ledit perçage et sur les alvéoles.This passage can be realized in different ways. According to a first embodiment, the axial retaining segments comprise an annular channel open laterally on said bore and on the cells.

Conformément à un autre mode de réalisation, les segments comportent des canaux radiaux réalisés notamment pas usinage.According to another embodiment, the segments comprise radial channels made in particular not machining.

D'autre caractéristiques et avantages ressortiront de la description qui suit de modes de réalisation en référence aux dessins annexés sur lesquels.

  • La figure 1 montre en coupe axiale une partie d'un moteur à turbine à gaz.
  • La figure 2 montre le montage des aubes sur un disque.
  • La figure 3 montre un montage de turbine BP de l'art antérieur avec circulation de l'air de ventilation des pieds des aubes.
  • La figure 4 montre un autre montage de turbine BP de l'art antérieur avec circulation de l'air de ventilation des pieds des aubes.
  • La figure 5 montre un tambour de turbine monobloc.
  • La figure 6 montre un tambour de turbine monobloc incorporant la solution de l'invention.
  • La figure 7 montre un détail de la figure 6 avec l'attache de pied d'aube.
  • La figure 8 montre une partie d'un segment de rétention axiale dans la solution conforme à l'invention.
  • La figure 9 montre une partie d'une variante de segment de rétention dans la solution conforme à l'invention.
Other features and advantages will become apparent from the following description of embodiments with reference to the accompanying drawings in which.
  • The figure 1 shows in axial section a part of a gas turbine engine.
  • The figure 2 shows the assembly of the blades on a disk.
  • The figure 3 shows a BP turbine assembly of the prior art with circulation of the ventilation air of the blade roots.
  • The figure 4 shows another BP turbine assembly of the prior art with circulation of the ventilation air of the blade roots.
  • The figure 5 shows a monobloc turbine drum.
  • The figure 6 shows a monobloc turbine drum incorporating the solution of the invention.
  • The figure 7 shows a detail of the figure 6 with the dawn foot tie.
  • The figure 8 shows part of an axial retention segment in the solution according to the invention.
  • The figure 9 shows a part of a variant of retention segment in the solution according to the invention.

En se reportant à la figure 6, on a représenté en coupe axiale une partie de la turbine BP incorporant la solution de l'invention. Le tambour monobloc 10 comprend les disques 11 et 12 reliés par une virole 13 et avec une virole arrière 14. Les éléments sont monoblocs en ce sens qu'ils sont, soit usinés pour former un tambour d'une pièce, soit soudés ensemble. La jante 12J du disque 12 comporte des alvéoles axiales dans lesquelles les pieds 6P des aubes 6 sont glissés axialement. Pour les caler axialement, les aubes comprennent un crochet 6B en aval de la face transversale arrière 6A du pied 6P.Referring to the figure 6 , there is shown in axial section a portion of the LP turbine incorporating the solution of the invention. The monobloc drum 10 comprises the discs 11 and 12 connected by a ferrule 13 and with a rear ferrule 14. The elements are monoblock in that they are either machined to form a drum in one piece, or welded together. The rim 12J of the disc 12 has axial recesses in which the feet 6P of the vanes 6 are slid axially. To wedge them axially, the blades comprise a hook 6B downstream of the rear transverse face 6A of the foot 6P.

De l'air doit circuler entre le volume interne du tambour 10 et le fond des alvéoles dans l'espace ménagé avec le pied des aubes pour en assurer la ventilation. Conformément à l'invention, on ménage un perçage 12P dans la paroi en aval de la jante 12J du disque à travers la virole 14 aval. Ce perçage est radial, il met en communication le volume intérieur tambour et le fond d'une rainure 12R'. Cette rainure est ouverte radialement. Elle est ménagée entre la jante 12J et une bride transversale parallèle à la jante 12J.Air must flow between the internal volume of the drum 10 and the bottom of the cells in the space provided with the blade root to ensure ventilation. In accordance with the invention, a 12P bore is provided in the downstream wall of the disk rim 12J through the downstream ferrule 14. This drilling is radial, it puts in communication the internal drum volume and the bottom of a groove 12R '. This groove is open radially. It is formed between the rim 12J and a transverse flange parallel to the rim 12J.

Les segments de rétention axiale 18 sont logés dans cette rainure 12R'. Ces segments en arc de cercle s'étendent radialement le long de la face aval de la jante et masquent les faces aval 6A des pieds 6P d'aubes. Les segments sont glissés entre la face aval 6A des pieds 6P et leur crochet aval correspondant. Ils bloquent de cette façon les pieds d'aube contre tout déplacement axial. La base 18B des segments est épaisse et occupe en largeur la rainure 12R'.The axial retention segments 18 are housed in this groove 12R '. These arcuate segments extend radially along the downstream face of the rim and mask the downstream faces 6A of the blade feet 6P. The segments are slid between the downstream face 6A 6P feet and their corresponding downstream hook. They block the feet of dawn in this way against any axial displacement. The base 18B of the segments is thick and occupies in width the groove 12R '.

Selon un premier mode réalisation, un canal annulaire 18C est usiné dans l'épaisseur de la base 18B. Ce canal met en communication les perçages 12P avec le fond des alvéoles et forme ainsi un passage 18P radial puis axial. En fonctionnement l'air circule depuis la zone amont du rotor de turbine. Il traverse le stator 20 par un passage 20P et se partage en plusieurs flux. Le flux F1 est guidé vers le passage ménagé entre la virole et une bride de fixation de la virole sur le premier disque 11 pour ventiler les alvéoles du disque 11. Une autre partie F2 du flux passe entre les ouvertures centrales de deux disques 11 et 12, et le stator 20, remonte le long de la face aval du disque 12 et s'engage dans les perçages 12P. Les perçages communiquant avec le fond de la rainure au droit du canal 18C, l'air se retrouve dans le canal annulaire 18C d'où il est distribué dans les espaces existants entre les pieds des aubes et le fond des alvéoles. En quittant cet espace, l'air est ensuite guidé dans la veine de gaz.According to a first embodiment, an annular channel 18C is machined in the thickness of the base 18B. This channel communicates the holes 12P with the bottom of the cells and thus forms a radial passage 18P and axial. In operation the air flows from the upstream zone of the turbine rotor. It passes through the stator 20 through a passage 20P and is divided into several streams. The flow F1 is guided towards the passage formed between the shell and a flange for attaching the ferrule to the first disk 11 to ventilate the cells of the disk 11. Another portion F2 of the flow passes between the central openings of two disks 11 and 12 , and the stator 20, goes up along the downstream face of the disk 12 and engages in the holes 12P. The holes communicating with the bottom of the groove in line with the channel 18C, the air is found in the annular channel 18C where it is distributed in the existing spaces between the blade roots and the bottom of the cells. Leaving this space, the air is then guided into the gas vein.

En perçant le tambour dans la zone située en aval de la jante du disque et en aménageant les segments de rétention axiale, on assure ainsi une alimentation en air de ventilation suffisante sans sacrifier à la résistance du disque. Le coût en masse est faible voir inexistant sur l'épaisseur de la base 18B. Le segment remplit sa fonction de rétention axiale sans perte d'efficacité.Drilling the drum in the area downstream of the rim of the disc and arranging the axial retention segments, thus ensures a sufficient ventilation air supply without sacrificing the strength of the disc. The cost in mass is low or non-existent on the thickness of the base 18B. The segment performs its function of axial retention without loss of efficiency.

Sur la figure 9, on a représenté une variante de réalisation du segment de rétention axiale. Ce segment 18', au lieu d'un canal continu formé dans la base 18'B, comprend une pluralité de lunules 18'C borgnes usinées dans la masse de la base 18'B. Ces lunules radiales communiquent d'un côté avec les perçages 12P et sont ouvertes axialement du côté de la face en appui contre la jante 12J au niveau des fonds d'alvéole. Elles forment les passages 18'P. La ventilation des attaches des aubes est assurée de la même façon que précédemment. L'air issu du distributeur amont de turbine circule à l'intérieur du tambour; une partie de ce flux est entraîné à travers les perçages 12P puis est guidé par les segments de rétention axiale dans les espaces libres entre les fonds d'alvéoles et les pieds des aubes.On the figure 9 there is shown an alternative embodiment of the axial retention segment. This segment 18 ', instead of a continuous channel formed in the base 18'B, comprises a plurality of blind 18'C blinds machined in the mass of the base 18'B. These radial lunulas communicate on one side with the holes 12P and are open axially on the side of the face bearing against the rim 12J at the cell bottom. They form the passages 18'P. The ventilation of the blades of the blades is provided in the same way as before. The air from the upstream turbine distributor circulates inside the drum; part of this flow is driven through the holes 12P and is guided by the axial retention segments in the free spaces between the cell bottoms and the blade roots.

Claims (8)

Dispositif d'alimentation en air de ventilation dans un rotor de turbine d'un moteur à turbine à gaz comportant un premier et un deuxième disques (11, 12) de turbine et une virole (14) en aval formant ensemble un tambour monobloc, le deuxième disque (12) de turbine comprenant des alvéoles usinées dans la jante (12J) pour loger les aubes (6) de turbine, les aubes étant retenues axialement par des segments (18 ; 18') de retenue axiale, caractérisé par le fait qu'au moins un perçage (12P) est réalisé dans la virole (14) en aval de la jante (12J) mettant en communication l'intérieur du tambour avec au moins une partie des dites alvéoles, un passage (18P ; 18'P) étant ménagé dans les segments (18 ; 18').Device for supplying ventilation air in a turbine rotor of a gas turbine engine comprising first and second turbine disks (11, 12) and a downstream shell (14) together forming a monoblock drum, the second turbine disk (12) comprising cavities machined in the rim (12J) for accommodating the turbine blades (6), the blades being retained axially by axial retention segments (18; 18 '), characterized in that at least one bore (12P) is formed in the shell (14) downstream of the rim (12J) placing the inside of the drum communication with at least a portion of said cells, a passage (18P; 18 ° P) being formed in the segments (18; 18 '). Dispositif selon la revendication précédente dont les segments (18 ; 18') de retenue axiale comportent un passage entre le perçage (12P) et les alvéoles du deuxième disque.Device according to the preceding claim wherein the segments (18; 18 ') of axial retention comprise a passage between the bore (12P) and the cells of the second disk. Dispositif selon la revendication 2 dont le passage est réalisé par usinage des segments (18 ; 18').Device according to claim 2, the passage of which is achieved by machining the segments (18; 18 '). Dispositif selon l'une des revendications précédentes dont les segments comprennent une base (18B; 18'B) logée dans une rainure (12R') ménagée dans le tambour.Device according to one of the preceding claims, the segments of which comprise a base (18B; 18'B) housed in a groove (12R ') formed in the drum. Dispositif selon la revendication précédente dont les segments (18) comprennent un canal annulaire (18C) dans la base (18B), le canal étant ouvert radialement sur les perçages (12P) et axialement sur les alvéoles de la jante (12J).Device according to the preceding claim, the segments (18) comprise an annular channel (18C) in the base (18B), the channel being open radially on the bores (12P) and axially on the cells of the rim (12J). Dispositif selon la revendication 4 dont les segments (18') comprennent une pluralité de lunules radiales (18'C) borgnes usinées dans la base (18'B).Device according to claim 4, wherein the segments (18 ') comprise a plurality of blind radial eyelets (18'C) machined in the base (18'B). Rotor de turbine de moteur à turbine à gaz comportant un dispositif d'alimentation en air de ventilation selon l'une des revendications 1 à 6.Gas turbine engine turbine rotor comprising a ventilation air supply device according to one of claims 1 to 6. Moteur à turbine à gaz comportant un rotor de turbine selon la revendication 7.Gas turbine engine comprising a turbine rotor according to claim 7.
EP08159726A 2007-07-06 2008-07-04 Device for supplying ventilation air to the vanes of a low-pressure turbine of a gas turbine engine Active EP2011966B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0704918A FR2918414B1 (en) 2007-07-06 2007-07-06 VENTILATION AIR SUPPLY DEVICE FOR LOW PRESSURE TURBINE BLADES OF A GAS TURBINE ENGINE; SEGMENT FOR AXIAL STOP AND VENTILATION OF LOW PRESSURE TURBINE BLADES

Publications (3)

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EP2011966A2 true EP2011966A2 (en) 2009-01-07
EP2011966A3 EP2011966A3 (en) 2010-03-03
EP2011966B1 EP2011966B1 (en) 2012-03-28

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EP (1) EP2011966B1 (en)
JP (1) JP5035146B2 (en)
CA (1) CA2636665C (en)
FR (1) FR2918414B1 (en)
RU (1) RU2481481C2 (en)

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FR2973433A1 (en) * 2011-04-04 2012-10-05 Snecma Turbine rotor for low pressure turbomachine e.g. turbojet of aircraft, has upstream and downstream disks arranged coaxially, and bearing unit supporting end portion of flange to prevent deviation of flange of downstream disk
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EP3026217A1 (en) * 2014-11-07 2016-06-01 United Technologies Corporation Turbine rotor or stator segmented sideplates with anti-rotation
EP3075952A1 (en) * 2015-03-31 2016-10-05 United Technologies Corporation Retaining rings for turbomachine disk and coverplate assemblies
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FR2965291A1 (en) * 2010-09-27 2012-03-30 Snecma Unitary assembly for disks of rotor of low pressure turbine of turboshaft engine e.g. turbojet engine, of airplane, has collar comprising downstream part that is formed with air passage openings opened in annular space
FR2973433A1 (en) * 2011-04-04 2012-10-05 Snecma Turbine rotor for low pressure turbomachine e.g. turbojet of aircraft, has upstream and downstream disks arranged coaxially, and bearing unit supporting end portion of flange to prevent deviation of flange of downstream disk
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FR2995021A1 (en) * 2012-09-04 2014-03-07 Snecma AIR SUPPLY DEVICE FOR AIRCRAFT ENGINE TURBINES
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GB2520212B (en) * 2012-09-04 2017-06-28 Snecma Air supply device for aircraft engine turbines
EP3026217A1 (en) * 2014-11-07 2016-06-01 United Technologies Corporation Turbine rotor or stator segmented sideplates with anti-rotation
US10408087B2 (en) 2014-11-07 2019-09-10 United Technologies Corporation Turbine rotor segmented sideplates with anti-rotation
EP3075952A1 (en) * 2015-03-31 2016-10-05 United Technologies Corporation Retaining rings for turbomachine disk and coverplate assemblies
US9732619B2 (en) 2015-03-31 2017-08-15 United Technologies Corporation Retaining rings for turbomachine disk and coverplate assemblies
EP3124742A1 (en) * 2015-07-28 2017-02-01 MTU Aero Engines GmbH Gas turbine
US10428656B2 (en) 2015-07-28 2019-10-01 MTU Aero Engines AG Gas turbine
FR3062677A1 (en) * 2017-02-07 2018-08-10 Safran Aircraft Engines DOUBLE FLOW TURBOREACTOR COMPRISING A PREVIOUS DISTRIBUTOR TWO FLOORS OF LOW PRESSURE TURBINES WHICH ARE VENTILATED BY COOLING AIR OF THE DISTRIBUTOR

Also Published As

Publication number Publication date
JP5035146B2 (en) 2012-09-26
FR2918414A1 (en) 2009-01-09
JP2009013981A (en) 2009-01-22
CA2636665C (en) 2015-02-24
US20090304495A1 (en) 2009-12-10
CA2636665A1 (en) 2009-01-06
RU2481481C2 (en) 2013-05-10
RU2008127152A (en) 2010-01-10
EP2011966A3 (en) 2010-03-03
EP2011966B1 (en) 2012-03-28
US8157506B2 (en) 2012-04-17
FR2918414B1 (en) 2013-04-12

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