EP0967364A1 - Stator ring for the high-pressure turbine of a turbomachine - Google Patents

Stator ring for the high-pressure turbine of a turbomachine Download PDF

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Publication number
EP0967364A1
EP0967364A1 EP99401567A EP99401567A EP0967364A1 EP 0967364 A1 EP0967364 A1 EP 0967364A1 EP 99401567 A EP99401567 A EP 99401567A EP 99401567 A EP99401567 A EP 99401567A EP 0967364 A1 EP0967364 A1 EP 0967364A1
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EP
European Patent Office
Prior art keywords
downstream
sectors
ring
spacer
foot
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
EP99401567A
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German (de)
French (fr)
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EP0967364B1 (en
Inventor
Alain Marc Lucien Broman
Léopold Jean Marie De Verduzan
Daniel Jean Marey
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
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Publication date
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Publication of EP0967364A1 publication Critical patent/EP0967364A1/en
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Publication of EP0967364B1 publication Critical patent/EP0967364B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to the stator of the high pressure turbine of a turbomachine. It concerns, in particular, the parts of the stator which face the moving blades of the rotor, especially at the first high pressure turbine stage.
  • the stator turbine casing 1 comprises parts annulars 2 which face the blades 3 of the rotor 4, at the entry of the high pressure turbine, downstream of the combustion chamber 5. These annular parts 2 of the turbine casing 1 therefore define a clearance with the top of the blades 3 of the stator 4, thus conditioning the efficiency of the turbomachine.
  • these annular parts 2 are supplied with gas at temperatures which allow either to expand or contract them to reduce to a minimum value the clearance existing between these vanes 3 and these annular parts 2, in order to thereby increase the yield of the turbomachine.
  • the gas is generally drawn from another part of the turbomachine, depending on the gas temperature or the speed of the rotor.
  • the annular part of the stator is composed of an internal crown which can be continuous, but which is generally formed of a series of 6 ring sectors facing the end of the blades 3 of the rotor. They are carried by a sector spacer 10 fixed to the turbine casing 1 and in which the at least one cavity 11 in contact with the ring sectors 6, with a view to proceed to thermal adjustment of these. Fixing these sectors ring 6 to the spacer sectors 10 of the stator is by clamps 7 placed on respective downstream flanges 8 and 9 of the ring sectors 6 and of the spacer sectors 10, these two flanges 8 and 9 being contiguous. On the upstream side, the fixing is done by an upstream flange 12 of each spacer sector 10 engaging in a groove 13 upstream of each of the ring sectors 6.
  • such a high pressure turbine of turbomachine can comprise several stages of this type, and consequently several stages of ring sectors and spacer parts.
  • the ring sectors 6 are located at the entrance to the high pressure turbine, in an area where the temperature can reach 1500 ° C. In therefore, they must be cooled.
  • the seal between these ring sectors 6 and spacer sectors 10 must be performed at better, in order to avoid the loss of part of the air flow of the turbomachine.
  • the fixing clips 7 help to partially ensure this seal.
  • air leaks and air flow taken from the engine to cool the ring sectors 6 can be relatively consistent.
  • the object of the invention is to remedy this drawback minimizing these leaks and the air flow taken from the engine, in order to to keep the value of the turbomachine good.
  • the downstream foot of the spacer sectors and the downstream flange of the ring sectors are bent and joined by radial junction surfaces which respectively extend the surface external of the downstream foot of the spacer sectors and the internal surface of the fixing flange of the downstream foot of the ring sectors, this allows form a 90 ° radial rim constituting an additional element operational with regard to sealing.
  • the clamps being placed around the downstream part of the assembly thus formed by the foot and the curved downstream flange of the spacer sectors and of the sectors ring.
  • the ring sectors include an upstream flange intended to be engaged in a corresponding groove of a foot upstream of the spacer sectors, in the purpose of securing, on the upstream side, the ring sectors on the spacer sectors.
  • FIG. 3 shows in detail the first embodiment of the high pressure turbine stator ring according to the invention.
  • the end of a blade 3 of the rotor which rotates opposite of the internal surface 21 of a ring sector 20 fixed to the stator by through the turbine housing 1.
  • This fixing is carried out by through spacer sectors 30 each fixed to the turbine housing 1.
  • the spacer sectors 30 therefore constitute a crown fixed fixing.
  • Figure 4 also allows you to see this crown spacer sectors 30 fixed to the turbine casing 1.
  • the number of sectors is relatively large.
  • This crown of sectors spacer 30 makes it possible to constitute an annular channel allowing a gas drawn from another part of the turbomachine to be in contact with Ring sectors 20 and influence their temperature.
  • this gas flow can enter the spacer sectors via a first orifice 33 for entering a first cavity 31 and into a second cavity 32 by a second orifice 34.
  • the gas flow taken upstream in the turbomachine can be in direct contact with the ring sectors 20 and influence their temperature.
  • This spacer sector 30 is fixed to the turbine casing 1 via an upstream fixing head 37M fitting into annular grooves 15M and by a downstream fixing head 37V inserting in a downstream groove 15V of the turbine casing 1.
  • each ring sector 20 is fixed relative to the spacer sector 30 by means of a upstream flange 23M fitting into an annular groove 38 of the foot upstream 35M from each spacer sector 30.
  • the fixing of the downstream side of the ring sectors is done by a downstream flange 23V of each ring sector 20 which is plated, by its downstream inner surface 24V against the downstream outer surface 37V 35V downstream foot of each spacer sector 30.
  • a characteristic important of the fixing according to the invention is that these two surfaces pressed against each other are bent upwards, i.e. towards the outside of the axis of rotation of the turbomachine. In the embodiment described in Figure 3, these two surfaces are perpendicular to this axis, that is to say that they constitute radial surfaces of junction. Maintaining in this position glued or plated one against the other of these two radial junction surfaces is produced by means of several fixing clips 40 placed around the entire circumference of all.
  • a first clamp tab 41 is housed in the hollow formed by the downstream external surface 36V of each spacer sector 30, while a second clamp leg 42 is pressed against the 25V downstream external surface of the downstream flange 23V.
  • the internal downstream surface 24V of each ring sector 20 is extended by curved perpendicular to the axis of the turbomachine. He is leaving similarly for the downstream external surface 37V of the downstream foot 35V, the end of the downstream foot of each spacer sector 30 and the downstream flange 23V of each ring sector 20 being of small thickness.
  • a second embodiment of the fixing the downstream foot 75V of the spacer sectors 70 and the sectors ring 20 can be made with a second kind of pliers fixing 60.
  • this clamp of fixing 60 can have a first clamp tab 61 coming to take support on the downstream external surface 76V of the spacer sector 70.
  • its second clamp leg 62 comes to bear against the 55V downstream external surface of the downstream flange 53V, at a place where this 55V downstream external surface is coaxial with the axis of the turbomachine.
  • the fixing clamp 60 comes to bear by its second clamp 62 on the downstream flange 53V, before its curved part.
  • a recess 63 inside the clamp 60, placed opposite the part curved with this downstream flange 53V, allows better tightening of the clamp 60 on the assembly and, in particular, on the downstream foot of each ring sector 20.
  • the main advantage of the invention is to obtain the best possible tightness at this high turbine ring pressure, in order to reduce the air flow taken from the turbomachine for the cooling of the ring sectors and thus to preserve a good value for the efficiency of this turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Abstract

The stator ring consists of holding sectors (30), of circular arc form and fixed to the inner wall of the turbine case (1). Each sector carries an upstream foot (35m) and a downstream foot (35v). A second inner ring (20) has its inner surface (21) forming the outer envelope for the rotation of the blades (3). The inner ring sectors also have feet (23m,23v), which interlock with the feet of the outer ring. The downstream feet of both rings are turned through 90 degrees and are fixed together by a series of grips (40).

Description

Domaine de l'inventionField of the invention

L'invention concerne le stator de la turbine haute pression d'une turbomachine. Elle concerne, en particulier, les parties du stator qui font face aux aubes mobiles du rotor, notamment au niveau du premier étage de la turbine haute pression.The invention relates to the stator of the high pressure turbine of a turbomachine. It concerns, in particular, the parts of the stator which face the moving blades of the rotor, especially at the first high pressure turbine stage.

Art antérieur et problème poséPrior art and problem posed

En référence à la figure 1, dans de nombreux exemples de turbomachines, le carter de turbine 1 du stator comprend des parties annulaires 2 qui font face aux aubes 3 du rotor 4, au niveau de l'entrée de la turbine haute pression, en aval de la chambre de combustion 5. Ces parties annulaires 2 du carter de turbine 1 définissent donc un jeu avec le sommet des aubes 3 du stator 4, conditionnant ainsi le rendement de la turbomachine.Referring to Figure 1, in many examples of turbomachinery, the stator turbine casing 1 comprises parts annulars 2 which face the blades 3 of the rotor 4, at the entry of the high pressure turbine, downstream of the combustion chamber 5. These annular parts 2 of the turbine casing 1 therefore define a clearance with the top of the blades 3 of the stator 4, thus conditioning the efficiency of the turbomachine.

Or, ces parties annulaires 2 sont alimentées en gaz à des températures qui permettent, soit de les dilater, soit des les contracter pour réduire à une valeur minimale le jeu existant entre ces aubes 3 et ces parties annulaires 2, dans le but d'accroítre ainsi le rendement de la turbomachine. Le gaz est généralement soutiré d'une autre partie de la turbomachine, en fonction de la température des gaz ou de la vitesse du rotor. However, these annular parts 2 are supplied with gas at temperatures which allow either to expand or contract them to reduce to a minimum value the clearance existing between these vanes 3 and these annular parts 2, in order to thereby increase the yield of the turbomachine. The gas is generally drawn from another part of the turbomachine, depending on the gas temperature or the speed of the rotor.

En référence à la figure 2, la partie annulaire du stator est composée d'une couronne interne qui peut être continue, mais qui est généralement formée d'une série de secteurs d'anneau 6 faisant face à l'extrémité des aubes 3 du rotor. Ils sont portés par un secteur d'entretoise 10 fixée au carter de turbine 1 et dans laquelle est formée au moins une cavité 11 en contact avec les secteurs d'anneau 6, en vue de procéder au réglage thermique de ceux-ci. La fixation de ces secteurs d'anneau 6 aux secteurs d'entretoise 10 du stator se fait par l'intermédiaire de pinces 7 placées sur des collerettes aval respectives 8 et 9 des secteurs d'anneau 6 et des secteurs d'entretoise 10, ces deux collerettes 8 et 9 étant jointives. Du côté amont, la fixation s'effectue par une collerette amont 12 de chaque secteur d'entretoise 10 s'engageant dans une rainure 13 amont de chacun des secteurs d'anneau 6.Referring to Figure 2, the annular part of the stator is composed of an internal crown which can be continuous, but which is generally formed of a series of 6 ring sectors facing the end of the blades 3 of the rotor. They are carried by a sector spacer 10 fixed to the turbine casing 1 and in which the at least one cavity 11 in contact with the ring sectors 6, with a view to proceed to thermal adjustment of these. Fixing these sectors ring 6 to the spacer sectors 10 of the stator is by clamps 7 placed on respective downstream flanges 8 and 9 of the ring sectors 6 and of the spacer sectors 10, these two flanges 8 and 9 being contiguous. On the upstream side, the fixing is done by an upstream flange 12 of each spacer sector 10 engaging in a groove 13 upstream of each of the ring sectors 6.

On note qu'une telle turbine haute pression de turbomachine peut comporter plusieurs étages de ce type, et par suite plusieurs étages de secteurs d'anneau et de parties d'entretoise. Les secteurs d'anneau 6 sont situés à l'entrée de la turbine haute pression, dans une zone où la température peut atteindre 1500°C. En conséquence, ils doivent être refroidis. D'autre part, l'étanchéité entre ces secteurs d'anneau 6 et les secteurs d'entretoise 10 doit être réalisée au mieux, afin d'éviter la perte d'une partie du débit d'air de la turbomachine. Les pinces de fixation 7 contribuent à assurer en partie cette étanchéité. Toutefois, compte tenu des dilatations dues aux différences de températures en fonctionnement, des fuites d'air ont lieu et le débit d'air prélevé sur le moteur pour refroidir les secteurs d'anneau 6 peut être relativement conséquent.It is noted that such a high pressure turbine of turbomachine can comprise several stages of this type, and consequently several stages of ring sectors and spacer parts. The ring sectors 6 are located at the entrance to the high pressure turbine, in an area where the temperature can reach 1500 ° C. In therefore, they must be cooled. On the other hand, the seal between these ring sectors 6 and spacer sectors 10 must be performed at better, in order to avoid the loss of part of the air flow of the turbomachine. The fixing clips 7 help to partially ensure this seal. However, given the expansions due to the differences in operating temperatures, air leaks and air flow taken from the engine to cool the ring sectors 6 can be relatively consistent.

Le but de l'invention est de remédier à cet inconvénient en minimisant ces fuites et le débit d'air prélevé sur le moteur, dans le but de conserver au rendement de la turbomachine une bonne valeur. The object of the invention is to remedy this drawback minimizing these leaks and the air flow taken from the engine, in order to to keep the value of the turbomachine good.

Résumé de l'inventionSummary of the invention

A cet effet, l'objet principal de l'invention est un anneau de stator de turbine haute pression d'une turbomachine comprenant un carter de turbine, l'anneau étant composé :

  • de secteurs d'entretoise en arc de cercle composant une entretoise en anneau, fermée sur 360°, fixée à la paroi interne du carter de turbine et possédant un pied amont et un pied aval ; et
  • des secteurs d'anneau en arc de cercle, composant un anneau fermé sur 360° pour faire face, par leur surface interne, à l'enveloppe développée par les extrémités des aubes de la roue de turbine haute pression en rotation, fixés au pied aval des secteurs d'entretoise, par une collerette aval fixée au pied aval des secteurs d'entretoise au moyen de pinces de fixation qui serrent ces deux types de secteurs les uns contre les autres par leurs pied aval et collerette aval.
To this end, the main object of the invention is a high pressure turbine stator ring of a turbomachine comprising a turbine housing, the ring being composed:
  • spacer sectors in an arc forming a ring spacer, closed over 360 °, fixed to the internal wall of the turbine casing and having an upstream foot and a downstream foot; and
  • ring sectors in an arc, forming a 360 ° closed ring to face, by their internal surface, the envelope developed by the ends of the blades of the rotating high pressure turbine wheel, fixed to the downstream foot spacer sectors, by a downstream flange fixed to the downstream foot of the spacer sectors by means of fixing clamps which clamp these two types of sectors against each other by their downstream foot and downstream flange.

Selon l'invention, le pied aval des secteurs d'entretoise et la collerette aval des secteurs d'anneau sont recourbés et jointifs par des surfaces radiales de jonction qui prolongent respectivement la surface externe du pied aval des secteurs d'entretoise et la surface interne de la collerette de fixation du pied aval des secteurs d'anneau, ceci permet de former un rebord radial à 90° constituant un élément supplémentaire opérationnel vis-à-vis de l'étanchéité. De plus, les pinces de fixation étant placées autour de la partie aval de l'ensemble ainsi formée par le pied et la collerette aval recourbés des secteurs d'entretoise et des secteurs d'anneau.According to the invention, the downstream foot of the spacer sectors and the downstream flange of the ring sectors are bent and joined by radial junction surfaces which respectively extend the surface external of the downstream foot of the spacer sectors and the internal surface of the fixing flange of the downstream foot of the ring sectors, this allows form a 90 ° radial rim constituting an additional element operational with regard to sealing. In addition, the clamps being placed around the downstream part of the assembly thus formed by the foot and the curved downstream flange of the spacer sectors and of the sectors ring.

Dans leur réalisation principale, les secteurs d'anneau comprennent une collerette amont destinée à être engagée dans une rainure correspondante d'un pied amont des secteurs d'entretoise, dans le but de réaliser la fixation, du côté amont, des secteurs d'anneau sur les secteurs d'entretoise.In their main realization, the ring sectors include an upstream flange intended to be engaged in a corresponding groove of a foot upstream of the spacer sectors, in the purpose of securing, on the upstream side, the ring sectors on the spacer sectors.

Dans une première utilisation des pinces de serrage, leurs surfaces de serrage prennent appui sur une partie recourbée de la surface externe du pied aval des secteurs d'entretoise et sur la partie recourbée de la surface externe des collerettes aval des secteurs d'anneau.In a first use of the collets, their clamping surfaces are supported on a curved part of the external surface of the downstream foot of the spacer sectors and on the part curved from the outer surface of the downstream flanges of the sectors ring.

Dans une deuxième utilisation des pinces de serrage, leur surface de serrage prennent appui sur une partie recourbée de la surface externe du pied aval des secteurs d'entretoise et sur la partie recourbée et la partie non recourbée de la surface externe des collerettes aval des secteurs d'anneau.In a second use of the collets, their clamping surface rests on a curved part of the surface external of the downstream foot of the spacer sectors and on the curved part and the non-curved part of the external surface of the downstream flanges of the ring areas.

Liste des figuresList of Figures

L'invention et ses différentes caractéristiques techniques seront mieux comprises à la lecture de la description suivante, d'une réalisation de l'invention, accompagnée de quelques figures représentant respectivement :

  • figure 1, en coupe, une turbomachine dans laquelle peut être utilisée l'invention ;
  • figure 2, en coupe, un anneau de stator de turbine haute pression selon l'art antérieur ;
  • figure 3, en coupe, un anneau de stator de turbine haute pression selon l'invention dans une première réalisation ;
  • figure 4, en vue cavalière partiellement coupée, l'anneau de stator de turbine haute pression selon l'invention de la figure 3 ; et
  • figure 5, en coupe partielle, un détail d'un anneau de stator de turbine haute pression dans une deuxième réalisation selon l'invention.
The invention and its various technical characteristics will be better understood on reading the following description of an embodiment of the invention, accompanied by a few figures representing respectively:
  • Figure 1, in section, a turbomachine in which the invention can be used;
  • Figure 2, in section, a high pressure turbine stator ring according to the prior art;
  • Figure 3, in section, a high pressure turbine stator ring according to the invention in a first embodiment;
  • Figure 4, in partially cut away view, the high pressure turbine stator ring according to the invention of Figure 3; and
  • Figure 5, in partial section, a detail of a high pressure turbine stator ring in a second embodiment according to the invention.

Description détaillée de deux réalisations de l'inventionDetailed description of two embodiments of the invention

La figure 3 représente en détail la première réalisation de l'anneau de stator de turbine haute pression selon l'invention. On retrouve sur cette figure 3, l'extrémité d'une aube 3 du rotor qui tourne en regard de la surface interne 21 d'un secteur d'anneau 20 fixé au stator par l'intermédiaire du carter de turbine 1. Cette fixation est réalisée par l'intermédiaire de secteurs d'entretoise 30 fixés eux-mêmes chacun au carter de turbine 1. Comme pour la réalisation selon l'art antérieur décrite à la figure 2, les secteurs d'entretoise 30 constituent donc une couronne fixe de fixation. La figure 4 permet d'ailleurs de bien voir cette couronne de secteurs d'entretoise 30 fixés au carter de turbine 1. Le nombre de secteurs est relativement important. Cette couronne de secteurs d'entretoise 30 permet de constituer un canal annulaire permettant à un gaz soutiré d'une autre partie de la turbomachine d'être en contact des secteurs d'anneau 20 et d'influer sur leur température.Figure 3 shows in detail the first embodiment of the high pressure turbine stator ring according to the invention. We find in this figure 3, the end of a blade 3 of the rotor which rotates opposite of the internal surface 21 of a ring sector 20 fixed to the stator by through the turbine housing 1. This fixing is carried out by through spacer sectors 30 each fixed to the turbine housing 1. As for the embodiment according to the prior art described in FIG. 2, the spacer sectors 30 therefore constitute a crown fixed fixing. Figure 4 also allows you to see this crown spacer sectors 30 fixed to the turbine casing 1. The number of sectors is relatively large. This crown of sectors spacer 30 makes it possible to constitute an annular channel allowing a gas drawn from another part of the turbomachine to be in contact with Ring sectors 20 and influence their temperature.

En se reportant de nouveau à la figure 3, on voit que ce flux de gaz peut pénétrer dans les secteurs d'entretoise par l'intermédiaire d'un premier orifice 33 pour pénétrer dans une première cavité 31 et dans une deuxième cavité 32 par un deuxième orifice 34. Ainsi, le flux de gaz prélevé en amont dans la turbomachine peut être en contact direct avec les secteurs d'anneau 20 et influer sur leur température.Referring again to Figure 3, we see that this gas flow can enter the spacer sectors via a first orifice 33 for entering a first cavity 31 and into a second cavity 32 by a second orifice 34. Thus, the gas flow taken upstream in the turbomachine can be in direct contact with the ring sectors 20 and influence their temperature.

Ce secteur d'entretoise 30 est fixé au carter de turbine 1 par l'intermédiaire d'une tête de fixation amont 37M s'insérant dans des rainures annulaires 15M et par une tête de fixation aval 37V s'insérant dans une rainure aval 15V du carter de turbine 1.This spacer sector 30 is fixed to the turbine casing 1 via an upstream fixing head 37M fitting into annular grooves 15M and by a downstream fixing head 37V inserting in a downstream groove 15V of the turbine casing 1.

Le côté amont 22M de chaque secteur d'anneau 20 est fixé par rapport au secteur d'entretoise 30 par l'intermédiaire d'une collerette amont 23M s'insérant dans une rainure annulaire 38 du pied amont 35M de chaque secteur d'entretoise 30.The upstream side 22M of each ring sector 20 is fixed relative to the spacer sector 30 by means of a upstream flange 23M fitting into an annular groove 38 of the foot upstream 35M from each spacer sector 30.

La fixation du côté aval des secteurs d'anneau se fait par une collerette aval 23V de chaque secteur d'anneau 20 qui est plaqué, par sa surface intérieure aval 24V contre la surface extérieure aval 37V du pied aval 35V de chaque secteur d'entretoise 30. Une caractéristique importante de la fixation selon l'invention est que ces deux surfaces plaquées l'une contre l'autre sont recourbées vers le haut, c'est-à-dire vers l'extérieur de l'axe de rotation de la turbomachine. Dans la réalisation décrite par la figure 3, ces deux surfaces sont perpendiculaires à cet axe, c'est-à-dire qu'elles constituent des surfaces radiales de jonction. Le maintien dans cette position collée ou plaquée l'une contre l'autre de ces deux surfaces radiales de jonction est réalisé au moyen de plusieurs pinces de fixation 40 placées sur toute la circonférence de l'ensemble. Une première patte de pince 41 vient se loger dans le creux formé par la surface externe aval 36V de chaque secteur d'entretoise 30, tandis qu'une deuxième patte de pince 42 vient se plaquer contre la surface externe aval 25V de la collerette aval 23V. En d'autres termes, la surface interne aval 24V de chaque secteur d'anneau 20 se prolonge de façon recourbée perpendiculairement à l'axe de la turbomachine. Il en va de même pour la surface externe aval 37V du pied aval 35V, l'extrémité du pied aval de chaque secteur d'entretoise 30 et la collerette aval 23V de chaque secteur d'anneau 20 étant de faible épaisseur.The fixing of the downstream side of the ring sectors is done by a downstream flange 23V of each ring sector 20 which is plated, by its downstream inner surface 24V against the downstream outer surface 37V 35V downstream foot of each spacer sector 30. A characteristic important of the fixing according to the invention is that these two surfaces pressed against each other are bent upwards, i.e. towards the outside of the axis of rotation of the turbomachine. In the embodiment described in Figure 3, these two surfaces are perpendicular to this axis, that is to say that they constitute radial surfaces of junction. Maintaining in this position glued or plated one against the other of these two radial junction surfaces is produced by means of several fixing clips 40 placed around the entire circumference of all. A first clamp tab 41 is housed in the hollow formed by the downstream external surface 36V of each spacer sector 30, while a second clamp leg 42 is pressed against the 25V downstream external surface of the downstream flange 23V. In other words, the internal downstream surface 24V of each ring sector 20 is extended by curved perpendicular to the axis of the turbomachine. He is leaving similarly for the downstream external surface 37V of the downstream foot 35V, the end of the downstream foot of each spacer sector 30 and the downstream flange 23V of each ring sector 20 being of small thickness.

Comme le montre la figure 3, il est préférable de maintenir les pinces de serrage 40 dans leur position de serrage, au moyen d'une goupille 50. Cette dernière traverse à la fois les pattes de pince 41 et 42 et les parties recourbées du pied aval 35V de chaque secteur d'entretoise 30 et de la collerette aval 23V de chaque secteur d'anneau 20. Ceci permet de s'affranchir de la force centrifuge qui a tendance à éjecter ces pinces de fixation 40 vers l'extérieur, c'est-à-dire vers le carter de turbine 1.As shown in Figure 3, it is best to maintain the collets 40 in their clamping position, by means of a pin 50. The latter passes through both the clamp legs 41 and 42 and the curved parts of the downstream foot 35V of each spacer sector 30 and the downstream flange 23V of each ring sector 20. This overcomes the centrifugal force which tends to eject these clamps 40 outward, i.e. to the turbine housing 1.

En référence à la figure 5, une deuxième réalisation de la fixation du pied aval 75V des secteurs d'entretoise 70 et des secteurs d'anneau 20 peut être réalisée avec une deuxième sorte de pince de fixation 60.With reference to FIG. 5, a second embodiment of the fixing the downstream foot 75V of the spacer sectors 70 and the sectors ring 20 can be made with a second kind of pliers fixing 60.

Comme dans la réalisation de la figure 3, cette pince de fixation 60 peut avoir une première patte de pince 61 venant prendre appui sur la surface externe aval 76V du secteur d'entretoise 70. Par contre, sa deuxième patte de pince 62 vient prendre appui contre la surface externe aval 55V de la collerette aval 53V, à un endroit où cette surface externe aval 55V est coaxiale avec l'axe de la turbomachine. En d'autres termes, la pince de fixation 60 vient prendre appui par sa deuxième pince 62 sur la collerette aval 53V, avant sa partie recourbée. Un évidement 63 à l'intérieur de la pince 60, placé en regard de la partie recourbée de cette collerette aval 53V, permet un meilleur serrage de la pince de fixation 60 sur l'ensemble et, notamment, sur le pied aval de chaque secteur d'anneau 20.As in the embodiment of FIG. 3, this clamp of fixing 60 can have a first clamp tab 61 coming to take support on the downstream external surface 76V of the spacer sector 70. By against, its second clamp leg 62 comes to bear against the 55V downstream external surface of the downstream flange 53V, at a place where this 55V downstream external surface is coaxial with the axis of the turbomachine. In in other words, the fixing clamp 60 comes to bear by its second clamp 62 on the downstream flange 53V, before its curved part. A recess 63 inside the clamp 60, placed opposite the part curved with this downstream flange 53V, allows better tightening of the clamp 60 on the assembly and, in particular, on the downstream foot of each ring sector 20.

Ainsi, on utilise un grand nombre de pinces de serrage sur toute la périphérie du montage entre les secteurs d'anneau 20 et les secteurs d'entretoise 70.Thus, a large number of collets are used over the entire periphery of the assembly between the ring sectors 20 and the spacer sectors 70.

Le principal avantage de l'invention est d'obtenir la meilleure étanchéité possible au niveau de cet anneau de turbine haute pression, dans le but de réduire le débit d'air prélevé sur la turbomachine pour le refroidissement des secteurs d'anneau et de conserver ainsi une bonne valeur du rendement de cette turbomachine.The main advantage of the invention is to obtain the best possible tightness at this high turbine ring pressure, in order to reduce the air flow taken from the turbomachine for the cooling of the ring sectors and thus to preserve a good value for the efficiency of this turbomachine.

Claims (4)

Anneau de stator de turbine haute pression d'une turbomachine, le stator comportant un carter de turbine (1) comportant par étage : des secteurs d'entretoise (30, 70) en arc de cercle composant une entretoise en anneau, fermée sur 360° et fixée à la paroi interne du carter de turbine (1) et possédant un pied amont (35M) et un pied aval (35V, 75V) ; et des secteurs d'anneau (20, 50) en arc de cercle composant un anneau fermé sur 360° pour faire face par leur surface interne (21) à l'enveloppe développée par les extrémités des aubes (3) des roues de la turbine, les secteurs d'anneau (20, 50) étant fixés au pied aval (35V, 75V) des secteurs d'entretoise (30, 70) par une collerette aval (23V, 53V) fixée au pied aval des secteurs d'entretoise (30, 70) au moyen de pinces de fixation (40, 60) qui serrent ces deux types de secteurs (20, 30, 50, 70) les uns contre les autres par leur pied aval et leur collerette aval (23V, 53V), l'extrémité du pied aval de chaque secteur d'entretoise (30, 70) et la collerette aval (23V, 53V) de chaque secteur d'anneau (20, 50) étant de faible épaisseur, caractérisé en ce que le pied aval (35V, 75V) des secteurs d'entretoise (30, 70) et les collerettes aval (23V, 53V) des secteurs d'anneau (30, 50) sont recourbés et jointifs par des surfaces radiales de jonction qui prolongent la surface externe (37V) du pied aval (35V, 75V) des secteurs d'entretoise (30, 70) et la surface interne (24V) de la collerette aval (23V, 53V) des secteurs d'anneau (30, 50) formant ainsi un rebord radial à 90° constituant un élément supplémentaire opérationnel vis-à-vis de l'étanchéité, les pinces de fixation (40, 60) étant placées autour de la partie aval de l'ensemble ainsi formé par le pied aval (35V, 75V) et la collerette aval (23V, 53V) recourbés des secteurs d'entretoise (30, 70) et des secteurs d'anneau (20, 50).High pressure turbine stator ring of a turbomachine, the stator comprising a turbine casing (1) comprising, per stage: spacer sectors (30, 70) in an arc forming a ring spacer, closed over 360 ° and fixed to the internal wall of the turbine casing (1) and having an upstream foot (35M) and a downstream foot ( 35V, 75V); and ring sectors (20, 50) in an arc forming a closed 360 ° ring to face by their internal surface (21) the envelope developed by the ends of the blades (3) of the turbine wheels, the ring sectors (20, 50) being fixed to the downstream foot (35V, 75V) of the spacer sectors (30, 70) by a downstream flange (23V, 53V) fixed to the downstream foot of the spacer sectors (30 , 70) by means of fixing clamps (40, 60) which clamp these two types of sectors (20, 30, 50, 70) against each other by their downstream foot and their downstream flange (23V, 53V), l the end of the downstream foot of each spacer sector (30, 70) and the downstream flange (23V, 53V) of each ring sector (20, 50) being thin, characterized in that the downstream foot (35V, 75V) of the spacer sectors (30, 70) and the downstream flanges (23V, 53V) of the ring sectors (30, 50) are bent and joined by radial surfaces of junction which extend the external surface (37V) of the downstream foot (35V, 75V) of the spacer sectors (30, 70) and the internal surface (24V) of the downstream flange (23V, 53V) of the ring sectors (30 , 50) thus forming a 90 ° radial rim constituting an additional operational element with regard to sealing, the fixing clamps (40, 60) being placed around the downstream part of the assembly thus formed by the downstream foot (35V, 75V) and the downstream flange (23V, 53V) curved between the spacer sectors (30, 70) and the ring sectors (20, 50). Anneau de stator selon la revendication 1, dans lequel la collerette amont (23M) des secteurs d'anneau (20) est destinée à être engagée dans une rainure correspondante (38) d'un pied amont (35M) des secteurs d'entretoise (30).The stator ring of claim 1, wherein the upstream flange (23M) of the ring sectors (20) is intended to be engaged in a corresponding groove (38) of an upstream foot (35M) spacer sectors (30). Anneau de stator selon la revendication 1, caractérisé en ce que les surfaces de serrage des pinces de fixation (40) prennent appui sur une partie recourbée de la surface externe (36V) du pied aval (35V) des secteurs d'entretoise (30) et sur la partie recourbée de la surface externe (25V) des collerettes aval (23V) des secteurs d'anneau (20).Stator ring according to claim 1, characterized in that the clamping surfaces of the clamps (40) take support on a curved part of the external surface (36V) of the downstream foot (35V) of the spacer sectors (30) and on the curved part of the external surface (25V) of the downstream flanges (23V) of the ring sectors (20). Anneau de stator selon la revendication 1, caractérisé en ce que les surfaces de serrage des pinces de fixation (60) prennent appui sur la partie recourbée de la surface externe (76V) du pied aval (75V) des secteurs d'entretoise (70) et sur la partie recourbée et la partie non recourbée de la surface externe (55V) de la collerette aval (53V) des secteurs d'anneau (50).Stator ring according to claim 1, characterized in that the clamping surfaces of the clamps (60) take support on the curved part of the external surface (76V) of the downstream foot (75V) of the spacer sectors (70) and on the curved part and the part not curved on the external surface (55V) of the downstream flange (53V) of the ring sectors (50).
EP99401567A 1998-06-25 1999-06-24 Stator ring for the high-pressure turbine of a turbomachine Expired - Lifetime EP0967364B1 (en)

Applications Claiming Priority (2)

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FR9808053 1998-06-25
FR9808053A FR2780443B1 (en) 1998-06-25 1998-06-25 HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE

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EP0967364A1 true EP0967364A1 (en) 1999-12-29
EP0967364B1 EP0967364B1 (en) 2004-10-06

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EP (1) EP0967364B1 (en)
JP (1) JP3912935B2 (en)
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FR (1) FR2780443B1 (en)

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Also Published As

Publication number Publication date
CA2276238C (en) 2008-10-14
FR2780443A1 (en) 1999-12-31
DE69920812T2 (en) 2005-10-13
DE69920812D1 (en) 2004-11-11
CA2276238A1 (en) 1999-12-25
EP0967364B1 (en) 2004-10-06
FR2780443B1 (en) 2000-08-04
US6200091B1 (en) 2001-03-13
JP3912935B2 (en) 2007-05-09
JP2000045707A (en) 2000-02-15

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