EP0967364B1 - 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
EP0967364B1
EP0967364B1 EP99401567A EP99401567A EP0967364B1 EP 0967364 B1 EP0967364 B1 EP 0967364B1 EP 99401567 A EP99401567 A EP 99401567A EP 99401567 A EP99401567 A EP 99401567A EP 0967364 B1 EP0967364 B1 EP 0967364B1
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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.)
Expired - Lifetime
Application number
EP99401567A
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German (de)
French (fr)
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EP0967364A1 (en
Inventor
Alain Marc Lucien Broman
Léopold Jean Marie De Verduzan
Daniel Jean Marey
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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Publication of EP0967364A1 publication Critical patent/EP0967364A1/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 blades of the rotor, especially at the level of the first stage of the high pressure turbine.
  • the turbine casing 1 of the stator comprises parts 2 which face the blades 3 of the rotor 4, at the level of the inlet of the high pressure turbine, downstream of the combustion chamber 5.
  • These annular parts 2 of the turbine casing 1 therefore define a game with the top of the blades 3 of the stator 4, thereby conditioning the efficiency of the turbine engine.
  • these annular parts 2 are supplied with gas to temperatures that allow them to be dilated or contracted to reduce to a minimum value the clearance between these blades 3 and these annular parts 2, in order to increase the performance of the turbine engine.
  • the gas is usually withdrawn from another part of the turbomachine, depending on the temperature of the gases or the speed of the rotor.
  • the annular portion of the stator is composed of an inner crown that can be continuous but which is generally formed of a series of ring sectors 6 facing the end of the blades 3 of the rotor. They are worn by a sector spacer 10 attached to the turbine casing 1 and in which is formed least one cavity 11 in contact with the ring sectors 6, with a view to proceed with the thermal adjustment of these.
  • the fixing of these sectors of ring 6 to the spacer sectors 10 of the stator is by via clips 7 placed on respective downstream flanges 8 and 9 ring sectors 6 and spacer sectors 10, these two flanges 8 and 9 being joined.
  • fixing is done by an upstream collar 12 of each spacer sector 10 engaging in a groove 13 upstream of each of the ring sectors 6.
  • such a high pressure turbine turbomachine may comprise several stages of this type, and consequently several stages of ring sectors and spacer parts.
  • the Ring sectors 6 are located at the inlet of the high pressure turbine, in an area where the temperature can reach 1500 ° C. In therefore, they must be cooled.
  • the tightness between these ring sectors 6 and the spacer sectors 10 must be realized at better, in order to avoid the loss of a part of the air flow of the turbomachine.
  • the securing clips 7 help to partially ensure this seal.
  • air leaks take place and the 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 by minimizing these leaks and the airflow taken from the engine, for the purpose to keep the performance of the turbomachine good value.
  • US-A-5 593 276 shows a sectorized ring of turbine stator, the side upstream of each sector being fixed by an axial upstream collar inserting in a groove of the upstream leg of a support ring fixed on the housing of turbine. Downstream side, a collar downstream of the ring sectors has an edge radial curved downstream cooperating with a downstream leg of the support ring and held by a C-clamp.
  • downstream foot of the spacer and the downstream flange of the ring sectors are curved thin and joined together by radial joining surfaces which respectively extend the surface external of the downstream foot of the spacer sectors and the inner surface of the collar for fixing the downstream leg of the ring sectors, this makes it possible to form a radial flange at 90 ° constituting an additional element operational vis-à-vis the sealing.
  • the fixing clamps being placed around the downstream part of the assembly thus formed by the foot and downstream flange curved of spacer sectors and sectors ring.
  • the ring areas comprise an upstream collar intended to be engaged in a corresponding groove of a foot upstream of the spacer sectors, in the purpose of achieving the fixing, on the upstream side, of 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 of the inner surface 21 of a ring sector 20 fixed to the stator by through the turbine casing 1.
  • This fixation is carried out by intermediate spacer sectors 30 themselves each attached to the turbine casing 1.
  • the spacer sectors 30 therefore constitute a crown fixed fixing.
  • Figure 4 allows to see this crown of spacer sectors 30 attached to the turbine casing 1.
  • the number of sectors is relatively important.
  • This crown of sectors spacer 30 makes it possible to constitute an annular channel allowing a gas withdrawn from another part of the turbomachine to be in contact with ring sectors 20 and affect their temperature.
  • this gas flow can penetrate the spacer sectors via of a first orifice 33 to enter a first cavity 31 and in a second cavity 32 by a second orifice 34.
  • the flow of gas taken upstream in the turbomachine can be in direct contact with ring sectors 20 and affect their temperature.
  • This spacer sector 30 is attached to the turbine casing 1 through an upstream mounting head 37M fitting into annular grooves 15M and 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 via a 23M upstream collar fitting into an annular groove 38 of the foot upstream 35M of each spacer sector 30.
  • Fixing 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 internal surface 24V against the downstream outer surface 37V downstream leg 35V of each spacer sector 30.
  • a characteristic important of the fixation according to the invention is that these two surfaces pressed against each other are curved upwards, ie towards the outside of the axis of rotation of the turbomachine. In the embodiment described in Figure 3, these two surfaces are perpendicular 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 joining surfaces is realized by means of several clamps 40 placed on the entire circumference of all.
  • a first clamp leg 41 is housed in the hollow formed by the downstream outer surface 36V of each spacer sector 30, while a second clamp tab 42 presses against the 25V downstream external surface of the downstream flange 23V.
  • the downstream internal surface 24V of each ring sector 20 is extended by curved way perpendicularly to the axis of the turbomachine. He is leaving likewise for the downstream external surface 37V of the downstream leg 35V, the end the downstream foot of each spacer sector 30 and the downstream flange 23V each ring sector 20 being thin.
  • a second embodiment of the fixing 75V downstream foot of spacer sectors 70 and sectors ring 20 can be made with a second kind of clamp of fixing 60.
  • fixation 60 may have a first gripper leg 61 to take support on the downstream external surface 76V of the spacer sector 70.
  • its second clamping lug 62 comes to bear against the downstream outer surface 55V of the downstream flange 53V, at a location where this Downstream external surface 55V is coaxial with the axis of the turbomachine.
  • the clamp 60 comes to bear by its second clamp 62 on the downstream flange 53V, before its curved portion.
  • a recess 63 inside the clamp 60, placed opposite the part curved downstream flange 53V, allows a better tightening of the fixing clamp 60 on the assembly and, in particular, on the downstream leg of each ring sector 20.
  • the main advantage of the invention is to obtain the better sealing possible at this high turbine ring pressure, in order to reduce the air flow taken from the turbomachine for cooling the ring sectors and thus keeping a good value of the performance 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)

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 blades of the rotor, especially at the level of the first stage of the high pressure turbine.

Art antérieur et problème poséPrior art and problem

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.With reference to FIG. 1, in numerous examples turbomachines, the turbine casing 1 of the stator comprises parts 2 which face the blades 3 of the rotor 4, at the level of the inlet of the high pressure turbine, downstream of the combustion chamber 5. These annular parts 2 of the turbine casing 1 therefore define a game with the top of the blades 3 of the stator 4, thereby conditioning the efficiency of the turbine engine.

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 to temperatures that allow them to be dilated or contracted to reduce to a minimum value the clearance between these blades 3 and these annular parts 2, in order to increase the performance of the turbine engine. The gas is usually withdrawn from another part of the turbomachine, depending on the temperature of the gases 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.With reference to FIG. 2, the annular portion of the stator is composed of an inner crown that can be continuous but which is generally formed of a series of ring sectors 6 facing the end of the blades 3 of the rotor. They are worn by a sector spacer 10 attached to the turbine casing 1 and in which is formed least one cavity 11 in contact with the ring sectors 6, with a view to proceed with the thermal adjustment of these. The fixing of these sectors of ring 6 to the spacer sectors 10 of the stator is by via clips 7 placed on respective downstream flanges 8 and 9 ring sectors 6 and spacer sectors 10, these two flanges 8 and 9 being joined. On the upstream side, fixing is done by an upstream collar 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 turbomachine may comprise several stages of this type, and consequently several stages of ring sectors and spacer parts. The Ring sectors 6 are located at the inlet of 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 tightness between these ring sectors 6 and the spacer sectors 10 must be realized at better, in order to avoid the loss of a part of the air flow of the turbomachine. The securing clips 7 help to partially ensure this seal. However, given the dilatations due to differences in operating temperatures, air leaks take place and the 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 by minimizing these leaks and the airflow taken from the engine, for the purpose to keep the performance of the turbomachine good value.

US-A-5 593 276 montre un anneau sectorisé de stator de turbine, le côté amont de chaque secteur étant fixé par une collerette amont axiale s'insérant dans une rainure du pied amont d'un anneau support fixé sur le carter de turbine. Côté aval, une collerette aval des secteurs d'anneau comporte un bord aval recourbé radial coopérant avec un pied aval de l'anneau support et maintenus par une pince de fixation en C.US-A-5 593 276 shows a sectorized ring of turbine stator, the side upstream of each sector being fixed by an axial upstream collar inserting in a groove of the upstream leg of a support ring fixed on the housing of turbine. Downstream side, a collar downstream of the ring sectors has an edge radial curved downstream cooperating with a downstream leg of the support ring and held by a C-clamp.

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.
For this purpose, the main object of the invention is a high-pressure turbine stator ring of a turbomachine comprising a turbine casing, the ring being composed of:
  • arcuate spacer sectors forming a ring spacer, closed 360 °, attached to the inner wall of the turbine casing and having an upstream leg and a downstream leg; and
  • arcuate ring sectors, 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, attached to the downstream leg spacer sectors, by a downstream flange fixed to the downstream end of the spacer sectors by means of clamps which clamp these two types of sectors against each other by their downstream foot and downstream flange.

En outre, le pied aval des secteurs d'entretoise et la collerette aval des secteurs d'anneau sont recourbés de faible épaisseur 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.In addition, the downstream foot of the spacer and the downstream flange of the ring sectors are curved thin and joined together by radial joining surfaces which respectively extend the surface external of the downstream foot of the spacer sectors and the inner surface of the collar for fixing the downstream leg of the ring sectors, this makes it possible to form a radial flange at 90 ° constituting an additional element operational vis-à-vis the sealing. In addition, the fixing clamps being placed around the downstream part of the assembly thus formed by the foot and downstream flange curved of spacer sectors and 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 achievement, the ring areas comprise an upstream collar intended to be engaged in a corresponding groove of a foot upstream of the spacer sectors, in the purpose of achieving the fixing, on the upstream side, of 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 clamps, their clamping surfaces rest on a curved part of the outer surface of the downstream foot of the spacer sectors and on the part curved of the outer surface of the downstream collars 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 clamps, their clamping surface bear on a bent part of the surface external of the downstream foot of the spacer sectors and on the bent portion and the non-curved portion of the outer surface of the downstream flanges of ring sectors.

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 features will be better understood on reading the following description of an embodiment of the invention, accompanied by a few figures respectively representing:
  • 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;
  • FIG. 4, partially broken off, the high-pressure turbine stator ring according to the invention of FIG. 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 of the inner surface 21 of a ring sector 20 fixed to the stator by through the turbine casing 1. This fixation is carried out by intermediate spacer sectors 30 themselves each attached to the turbine casing 1. As for the embodiment according to the prior art described in Figure 2, the spacer sectors 30 therefore constitute a crown fixed fixing. Figure 4 allows to see this crown of spacer sectors 30 attached to the turbine casing 1. The number of sectors is relatively important. This crown of sectors spacer 30 makes it possible to constitute an annular channel allowing a gas withdrawn from another part of the turbomachine to be in contact with ring sectors 20 and affect 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 back to Figure 3, we see that this gas flow can penetrate the spacer sectors via of a first orifice 33 to enter a first cavity 31 and in a second cavity 32 by a second orifice 34. Thus, the flow of gas taken upstream in the turbomachine can be in direct contact with ring sectors 20 and affect 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 attached to the turbine casing 1 through an upstream mounting head 37M fitting into annular grooves 15M and 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 via a 23M upstream collar fitting into an annular groove 38 of the foot upstream 35M of 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.Fixing 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 internal surface 24V against the downstream outer surface 37V downstream leg 35V of each spacer sector 30. A characteristic important of the fixation according to the invention is that these two surfaces pressed against each other are curved upwards, ie towards the outside of the axis of rotation of the turbomachine. In the embodiment described in Figure 3, these two surfaces are perpendicular 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 joining surfaces is realized by means of several clamps 40 placed on the entire circumference of all. A first clamp leg 41 is housed in the hollow formed by the downstream outer surface 36V of each spacer sector 30, while a second clamp tab 42 presses against the 25V downstream external surface of the downstream flange 23V. In other words, the downstream internal surface 24V of each ring sector 20 is extended by curved way perpendicularly to the axis of the turbomachine. He is leaving likewise for the downstream external surface 37V of the downstream leg 35V, the end the downstream foot of each spacer sector 30 and the downstream flange 23V each ring sector 20 being thin.

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 tongs 41 and 42 and the bent parts of the downstream leg 35V of each spacer sector 30 and the downstream flange 23V of each ring sector 20. This allows to get rid of the centrifugal force that tends to eject these clamps 40 to the outside, that is to say towards the turbine casing 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 75V downstream foot of spacer sectors 70 and sectors ring 20 can be made with a second kind of clamp of 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. fixation 60 may have a first gripper leg 61 to take support on the downstream external surface 76V of the spacer sector 70. By against, its second clamping lug 62 comes to bear against the downstream outer surface 55V of the downstream flange 53V, at a location where this Downstream external surface 55V is coaxial with the axis of the turbomachine. In in other words, the clamp 60 comes to bear by its second clamp 62 on the downstream flange 53V, before its curved portion. A recess 63 inside the clamp 60, placed opposite the part curved downstream flange 53V, allows a better tightening of the fixing clamp 60 on the assembly and, in particular, on the downstream leg 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 better sealing possible at this high turbine ring pressure, in order to reduce the air flow taken from the turbomachine for cooling the ring sectors and thus keeping a good value of the performance of this turbomachine.

Claims (4)

  1. Stator ring for a high-pressure turbine of a turbo engine, the stator comprising a turbine casing (1) comprising per stage:
    circular-arc-shaped spacer sectors (30, 70), forming a spacer ring, closed over 360° and fixed to the inner wall of the turbine casing (1) and possessing an upstream foot (35M) and a downstream foot (35V, 75V); and
    circular-arc-shaped ring sectors (20), forming a ring closed over 360° so as to face with their inner surface (21) the shell generated by the ends of the vanes (3) of the wheels of the turbine, the ring sectors (20) being fixed to the downstream foot (35V, 75V) of the spacer sectors (30, 70) by a downstream collar (23V, 53V) fixed to the downstream foot of the spacer sectors (30, 70) by means of fastening clamps (40, 60) which clamp these two types of sectors (20, 30, 70) one against the other by their downstream foot and their downstream collar (23V, 53V),
       in which the downstream foot (35V, 75V) of the spacer sectors (30, 70) and the downstream collars (23V, 53V) of the ring sectors (20) are curved and are joined by radial joining surfaces extending the outer surface (37V) of the downstream foot (35V, 75V) of the spacer sectors (30, 70) and the inner surface (24V) of the downstream collar (23V, 53V) of the ring sectors (20), the radial, curved downstream ends of the downstream foot of each spacer sector (30, 70) and the downstream collar (23V, 53V) of each ring sector (20) being small in thickness, thus forming a 90° radial flange constituting a supplementary element having a sealing function, the fastening clamps (40, 60) being placed around the downstream portion of the assembly thus formed by the downstream foot (35V, 75V) and the curved downstream collar (23V, 53V) of the spacer sectors (30, 70) and of the ring sectors (20, 50).
  2. Stator ring according to Claim 1, in which the upstream collar (23M) of the ring sectors (20) is intended to be engaged in a corresponding groove (38) in an upstream foot (35M) of the spacer sectors (30).
  3. Stator ring according to Claim 1, characterized in that the clamping surfaces of the fastening clamps (40) bear upon a curved portion of the outer surface (36V) of the downstream foot (35V) of the spacer sectors (30) and upon the curved portion of the outer surface (25V) of the downstream collars (23V) of the ring sectors (20).
  4. Stator ring according to Claim 1, characterized in that the clamping surfaces of the fastening clamps (60) bear upon the curved portion of the outer surface (76V) of the downstream foot (75V) of the spacer sectors (70) and upon the curved portion and the non-curved portion of the outer surface (55V) of the downstream collar (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)

Application Number Priority Date Filing Date Title
FR9808053A FR2780443B1 (en) 1998-06-25 1998-06-25 HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE
FR9808053 1998-06-25

Publications (2)

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

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EP99401567A Expired - Lifetime EP0967364B1 (en) 1998-06-25 1999-06-24 Stator ring for the high-pressure turbine of a turbomachine

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US (1) US6200091B1 (en)
EP (1) EP0967364B1 (en)
JP (1) JP3912935B2 (en)
CA (1) CA2276238C (en)
DE (1) DE69920812T2 (en)
FR (1) FR2780443B1 (en)

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Also Published As

Publication number Publication date
DE69920812T2 (en) 2005-10-13
FR2780443B1 (en) 2000-08-04
JP3912935B2 (en) 2007-05-09
EP0967364A1 (en) 1999-12-29
CA2276238C (en) 2008-10-14
CA2276238A1 (en) 1999-12-25
US6200091B1 (en) 2001-03-13
JP2000045707A (en) 2000-02-15
DE69920812D1 (en) 2004-11-11
FR2780443A1 (en) 1999-12-31

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