EP1793093A2 - Improved turbomachine turbine nozzle - Google Patents

Improved turbomachine turbine nozzle Download PDF

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Publication number
EP1793093A2
EP1793093A2 EP06077140A EP06077140A EP1793093A2 EP 1793093 A2 EP1793093 A2 EP 1793093A2 EP 06077140 A EP06077140 A EP 06077140A EP 06077140 A EP06077140 A EP 06077140A EP 1793093 A2 EP1793093 A2 EP 1793093A2
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EP
European Patent Office
Prior art keywords
distributor
sector
platforms
flange
fixed
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
EP06077140A
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German (de)
French (fr)
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EP1793093A3 (en
EP1793093B1 (en
Inventor
Alexandre Nicolas Dervaux
Patrick Joseph Marie Girard
Gael Loro
Guillaume Jean-Claude Robert Renon
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP1793093A2 publication Critical patent/EP1793093A2/en
Publication of EP1793093A3 publication Critical patent/EP1793093A3/en
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Publication of EP1793093B1 publication Critical patent/EP1793093B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • the present invention relates to the field of turbomachines, in particular an improved turbomachine turbine distributor.
  • An aviation turbine engine typically comprises a compressor, a combustion chamber and a turbine.
  • the role of the turbine is to ensure the rotational drive of the compressor by taking a portion of the pressure energy of the hot gases leaving the combustion chamber and converting it into mechanical energy.
  • the turbine located downstream of the combustion chamber, is the organ of the turbomachine that works in the most severe conditions. It is particularly subjected to significant thermal and mechanical stresses generated by the hot gases at the chamber outlet.
  • An axial turbine conventionally comprises at least one distributor, consisting of a vanes grid fixed relative to the casing of the turbomachine, and at least one movable wheel, comprising a set of vanes capable of being rotated.
  • the nozzle vanes are generally fixed radially with respect to the axis of rotation of the turbomachine on two concentric annular shrouds, called inner shroud and outer shroud, one end of the blades being integral with the inner shroud and another end of the blades being integral with the outer shell.
  • the dispenser may be sectored, each sector being provided with a plurality of blades.
  • the distributor sectors are fixed on a fixed annular casing.
  • the assembly of a plurality of identical sectors connected end to end ring on a fixed annular casing makes it possible to reconstitute the distributor.
  • the valve sectors comprise an axis of revolution coaxial with the axis of rotation of the turbomachine.
  • the inner ferrule and outer ferrule portions are respectively called inner platform and outer deck.
  • the space defined between the inner platform and the platform Outer is a stream of air in which flows air from the combustion chamber.
  • the platforms have portions exposed directly to the air stream and other unexposed portions.
  • the hot gas-exposed portions such as the surfaces delimiting the airstream, will expand more rapidly than the unexposed portions, such as flanges described in detail below.
  • the platforms are more massive parts than the blades. Consequently, the platforms have a greater thermal inertia than the blades, which implies two consequences: under the effect of an increase in temperature, the blades will, on the one hand, expand more rapidly than the blades. platforms, and on the other hand, the platforms will impose their deformation at the blades. This phenomenon is also called bimetallic effect.
  • the distributor undergoes heating and cooling deforming the inner and outer platforms. Under the effect of these deformations, the vanes of the distributor are subjected to a succession of traction and compression which induce the appearance of cracks affecting the life of the blades.
  • the present invention aims to solve the aforementioned problems by providing a distributor having more flexibility.
  • the invention relates to a turbomachine turbine nozzle sector comprising an inner platform and an outer platform, at least one blade fixed between said platforms, at least one of said platforms comprising at least one flaccid having a first end fixed to the platform and a second free end, characterized in that said flange comprises at least one free softening recess.
  • the flange may be either a radial flange or a semi-cylindrical flange.
  • this recess is made in a non-opening way.
  • such a recess can easily relate to existing distributor sectors by different known machining techniques. It is therefore possible to relax the distributor sectors already in circulation.
  • the present application therefore also relates to a distributor sector softening process characterized in that it consists in machining at least one non-opening recess in at least one flange of a distributor sector.
  • Figure 1 illustrates, in a sectional view, a distributor sector 1 installed on a turbomachine. At least one guide vane 2 is fixed on this distributor sector 1 radially with respect to the axis of revolution X of said distributor sector 1, between an inner platform 3 and an outer platform 4. On a radial axis Y orthogonally cutting the axis of revolution X, an inner platform 3 is located at a smaller distance from this axis X than an outer platform 4.
  • This blade 2 is directly exposed to hot gases from the combustion chamber.
  • the platforms 3 and 4 comprise parts exposed directly to the air from the combustion chamber, in particular the surfaces 3a and 4a delimiting the air stream 12, and other parts not exposed to this air.
  • Figures 2, 3 and 4 show different operating phases of a distributor sector 1.
  • FIG. 2 schematically illustrates a distributor sector 1 at rest, that is to say when the turbine engine is at a standstill. No thermal or mechanical stress is exerted on the distributor sector 1.
  • FIG 3 schematically illustrates a distributor sector 1 during a warm-up phase.
  • the warm-up phase the most important during a flight, is noted at the time of takeoff of the aircraft.
  • the inner 3 and outer 4 platforms deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become convex with respect to this vein 12.
  • the blades 2a located in the center of the dispenser sector 1 undergo compression and that the blades 2b located at the periphery are subjected to traction.
  • Figure 4 schematically illustrates a distributor sector 1 during a cooling phase.
  • the inner platforms 3 and outer 4 deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become concave facing this vein 12.
  • the blades 2a located in the center of the dispenser sector 1 are pulled and the blades 2b at the periphery undergo compression.
  • the deformations of the inner platforms 3 and outer 4 promote the appearance of cracks on the distributor areas. It is therefore necessary to reduce the deformation of the platforms 3 and 4 to increase the service life of the valve sectors and in particular blades 2, a blade being generally the part with the shortest service life on a distributor sector 1 .
  • the platforms 3 or 4 of a distributor sector 1 may comprise at least one so-called radial flange 5 or at least one semi-cylindrical flange 6, as represented in FIGS. 5 and 6.
  • a flange 5 or 6 comprises a first end 5a or 6a fixed on the platform 3 or 4 and a second free end 5b or 6b, that is to say a non-fixed end on the platform 3 or 4.
  • a radial flange 5 extends in a plane orthogonally intersecting the axis of revolution X of the distributor sector 1.
  • the radial flange 5 provides axial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1.
  • the axial locking is the limitation of any translational movement of the distributor sector 1 relative to the fixed annular casing 13 in a direction parallel to the axis of revolution X.
  • a semi-cylindrical flange 6 extends cylindrically with respect to the axis of revolution X of the distributor sector 1.
  • a flange is semi-cylindrical in that it extends only over a portion of a cylinder corresponding to a distributor sector.
  • the semi-cylindrical flange 6 provides a radial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1.
  • the radial blocking is the limitation of any translational movement of the distributor sector 1 in a direction of a radial axis Y orthogonally cutting the axis of revolution X.
  • At least one locking means on these flanges allows the tangential locking relative to the fixed annular casing 13, the latter comprising a complementary means cooperating with the tangential blocking means.
  • Tangential blocking is the limitation of any lateral movement of a manifold sector 1 to the adjacent manifold sectors.
  • This tangential blocking means may be a notch 7 intended to cooperate with a complementary lug 8 on the fixed annular casing 13 of the turbomachine, as shown in FIG. 5, or, conversely, a lug intended to cooperate with a notch complementary to the fixed annular casing 13 of the turbomachine.
  • At least one flange 5 or 6 of the distributor sector 1 further comprises at least one non-emerging free softening recess.
  • a recess is a removal of material in a room. It can be opening or not.
  • the term "free recess” means a recess which is not intended for cooperate with complementary means, for example to ensure any blocking.
  • FIG. 5 represents an outer platform 4 of distributor sector 1 comprising a radial flange 5 and semi-cylindrical flanges 6. These flanges 5 or 6 may also be present on an inner platform 3.
  • the inner platform 3, operating according to the same principles, will not be described in detail.
  • the recess 9 is open and is in the form of a notch 9.
  • These notches 9 soften the platform 4 of the distributor sector 1. They reduce the sensitivity of the blades to the deformations of the sector. Distributor 1 evoked above-high and increase its service life.
  • these free softening notches 9 are located on the second free end 5b or 6b of a flange 5 or 6.
  • Such opening openings are known documents US 3781125 and US 6210108 .
  • FIG. 6 represents an outer platform 4 of distributor sector 1, according to the invention, comprising a radial flange 5 and semi-cylindrical flanges 6.
  • the recess 10 is non-opening. These recesses 10 consist of recesses 10 made on the flanges 5 and 6 of the distributor sector 1. Such recesses 10 also make it possible to improve the resistance to the deformations referred to above of the distributor sector 1 and to increase its duration. life. Preferably, these recesses 10 are located on the first end 5a or 6a, fixed on the platform 3 or 4, of a flange 5 or 6.
  • Each distributor sector 1 is fixed on a fixed annular casing 13 of the turbomachine.
  • the assembly of the distributor sectors 1 and the annular housing 13 constitutes a turbine distributor.
  • These recesses 10 can be obtained by different machining techniques known per se.
  • these recesses 10 can be realized on existing distributor sectors. It is therefore possible to relax the distributor sectors already in circulation.
  • the present application also relates to a method of softening a distributor sector 1 comprising at least one blade 2 and at least one flange 5 or 6 characterized in that it consists in machining at least one recess 10 in at least one flange 5 or 6 of the distributor sector 1.

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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)

Abstract

The turbine distributor sector, comprising inner and outer (4) platforms with blades fixed between them, has one or more flanges (5, 6) fixed by one end (5a, 6a) to at least one of the platforms and made with recesses (10) to give them flexibility. The recesses are in the form of hollows in the ends of the flanges fixed to the platforms but do not pass through the flanges. One of the flanges (5) extends in a radial plane relative to the turbine sector's axis of revolution, while the other (6) is semicylindrical relative to the same axis.

Description

La présente invention concerne le domaine des turbomachines, en particulier un distributeur de turbine de turbomachine amélioré.The present invention relates to the field of turbomachines, in particular an improved turbomachine turbine distributor.

Une turbomachine aéronautique comporte classiquement un compresseur, une chambre de combustion et une turbine. Le rôle de la turbine est d'assurer l'entraînement en rotation du compresseur en prélevant une partie de l'énergie de pression des gaz chauds sortant de la chambre de combustion et en la transformant en énergie mécanique.An aviation turbine engine typically comprises a compressor, a combustion chamber and a turbine. The role of the turbine is to ensure the rotational drive of the compressor by taking a portion of the pressure energy of the hot gases leaving the combustion chamber and converting it into mechanical energy.

La turbine, située en aval de la chambre de combustion, est l'organe de la turbomachine qui travaille dans les conditions les plus sévères. Elle est notamment soumise à des contraintes thermiques et mécaniques importantes générées par les gaz chauds en sortie de chambre.The turbine, located downstream of the combustion chamber, is the organ of the turbomachine that works in the most severe conditions. It is particularly subjected to significant thermal and mechanical stresses generated by the hot gases at the chamber outlet.

Une turbine axiale comprend classiquement au moins un distributeur, constitué d'une grille d'aubes fixes par rapport au carter de la turbomachine, et au moins une roue mobile, comportant un ensemble d'aubes susceptible d'être mis en rotation.An axial turbine conventionally comprises at least one distributor, consisting of a vanes grid fixed relative to the casing of the turbomachine, and at least one movable wheel, comprising a set of vanes capable of being rotated.

Les aubes de distributeur sont en général fixées radialement par rapport à l'axe de rotation de la turbomachine sur deux viroles annulaires concentriques, dites virole interne et virole externe, une extrémité des aubes étant solidaire de la virole interne et une autre extrémité des aubes étant solidaire de la virole externe.The nozzle vanes are generally fixed radially with respect to the axis of rotation of the turbomachine on two concentric annular shrouds, called inner shroud and outer shroud, one end of the blades being integral with the inner shroud and another end of the blades being integral with the outer shell.

Le distributeur peut être sectorisé, chaque secteur étant muni d'une pluralité d'aubes. Sur une turbomachine, les secteurs de distributeur sont fixés sur un carter annulaire fixe. L'assemblage d'une pluralité de secteurs identiques reliés bout à bout en anneau sur un carter annulaire fixe permet de reconstituer le distributeur. Les secteurs de distributeurs comportent un axe de révolution coaxial à l'axe de rotation de la turbomachine.The dispenser may be sectored, each sector being provided with a plurality of blades. On a turbomachine, the distributor sectors are fixed on a fixed annular casing. The assembly of a plurality of identical sectors connected end to end ring on a fixed annular casing makes it possible to reconstitute the distributor. The valve sectors comprise an axis of revolution coaxial with the axis of rotation of the turbomachine.

Sur un secteur de distributeur, les portions de virole interne et de virole externe sont respectivement appelées plate-forme intérieure et plate-forme extérieure. L'espace défini entre la plate-forme intérieure et la plate-forme extérieure constitue une veine d'air dans laquelle d'écoule de l'air en provenance de la chambre de combustion.On a dispenser sector, the inner ferrule and outer ferrule portions are respectively called inner platform and outer deck. The space defined between the inner platform and the platform Outer is a stream of air in which flows air from the combustion chamber.

Les plates-formes comportent des parties exposées directement à la veine d'air et d'autres parties non exposées. Par conséquent, les parties exposées aux gaz chauds, telles que les surfaces délimitant la veine d'air, vont se dilater plus rapidement que les parties non exposées, telles que des flasques décrits en détail plus-bas.The platforms have portions exposed directly to the air stream and other unexposed portions. As a result, the hot gas-exposed portions, such as the surfaces delimiting the airstream, will expand more rapidly than the unexposed portions, such as flanges described in detail below.

Par ailleurs, les plates-formes sont des pièces plus massives que les aubes. Par conséquent, les plates-formes ont une inertie thermique plus importante que les aubes, ce qui implique deux conséquences : sous l'effet d'une augmentation de la température, les aubes vont, d'une part, se dilater plus rapidement que les plates-formes, et d'autre part, les plates-formes vont imposer leur déformation aux aubes. Ce phénomène est aussi appelé effet bilame.In addition, the platforms are more massive parts than the blades. Consequently, the platforms have a greater thermal inertia than the blades, which implies two consequences: under the effect of an increase in temperature, the blades will, on the one hand, expand more rapidly than the blades. platforms, and on the other hand, the platforms will impose their deformation at the blades. This phenomenon is also called bimetallic effect.

Pendant les différentes phases du vol d'un aéronef équipé d'une turbomachine, le distributeur subi des échauffements et des refroidissements déformant les plates-formes intérieure et extérieure. Sous l'effet de ces déformations, les aubes du distributeur sont soumises à une succession de traction et de compression qui induisent l'apparition de criques nuisant à la durée de vie des aubes.During the various phases of the flight of an aircraft equipped with a turbomachine, the distributor undergoes heating and cooling deforming the inner and outer platforms. Under the effect of these deformations, the vanes of the distributor are subjected to a succession of traction and compression which induce the appearance of cracks affecting the life of the blades.

Pour résoudre ces problèmes, une solution connue de l'art antérieur consiste à concevoir des secteurs de distributeur avec des plates-formes peu massives. Toutefois cette solution est loin d'être satisfaisante puisque la tenue mécanique de tels secteurs de distributeur en est affectée.To solve these problems, a known solution of the prior art is to design distributor sectors with low mass platforms. However, this solution is far from satisfactory since the mechanical strength of such distributor sectors is affected.

La présente invention a pour objectif de résoudre les problèmes précités en proposant un distributeur présentant plus de souplesse.The present invention aims to solve the aforementioned problems by providing a distributor having more flexibility.

Pour cela, l'invention concerne un secteur de distributeur de turbine de turbomachine comportant une plate-forme intérieure et une plate-forme extérieure, au moins une aube fixée entre lesdites plates-formes, au moins une desdites plates-formes comportant au moins un flasque, ayant une première extrémité fixée sur la plate-forme et une seconde extrémité libre, caractérisé en ce que ledit flasque comporte au moins un évidement d'assouplissement libre.For this, the invention relates to a turbomachine turbine nozzle sector comprising an inner platform and an outer platform, at least one blade fixed between said platforms, at least one of said platforms comprising at least one flaccid having a first end fixed to the platform and a second free end, characterized in that said flange comprises at least one free softening recess.

Le flasque peut être soit un flasque radial soit un flasque semi-cylindrique.The flange may be either a radial flange or a semi-cylindrical flange.

Selon l'invention, cet évidement est réalisé de manière non-débouchant.According to the invention, this recess is made in a non-opening way.

Avantageusement, un tel évidement peut se rapporter facilement sur des secteurs de distributeurs déjà existants par différentes techniques d'usinage connues. Il est donc possible d'assouplir des secteurs de distributeur déjà mis en circulation.Advantageously, such a recess can easily relate to existing distributor sectors by different known machining techniques. It is therefore possible to relax the distributor sectors already in circulation.

La présente demande concerne donc également un procédé d'assouplissement de secteurs de distributeur caractérisé en qu'il consiste à usiner au moins un évidement non-débouchant dans au moins un flasque d'un secteur de distributeur.The present application therefore also relates to a distributor sector softening process characterized in that it consists in machining at least one non-opening recess in at least one flange of a distributor sector.

L'invention sera mieux comprise et d'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la suite de la description, donnée à titre d'exemple non limitatif, en référence aux dessins annexés qui représentent respectivement :

  • Figure 1, une vue en coupe de la région d'une turbomachine dans laquelle est localisé le secteur de distributeur ;
  • Figure 2; une vue schématique d'un secteur de distributeur au repos ;
  • Figure 3; une vue schématique d'un secteur de distributeur pendant une phase d'échauffement ;
  • Figure 4 ; une vue schématique d'un secteur de distributeur pendant une phase de refroidissement ;
  • Figure 5 ; une vue en perspective d'une plate-forme extérieure d'un secteur de distributeur comportant des évidements débouchant; et
  • Figure 6 ; une vue en perspective d'une plate-forme extérieure d'un secteur de distributeur comportant des évidements non-débouchant selon l'invention ;
The invention will be better understood and other features and advantages of the invention will appear on reading the following description, given by way of non-limiting example, with reference to the accompanying drawings which respectively represent:
  • Figure 1 is a sectional view of the region of a turbomachine in which is located the distributor sector;
  • Figure 2; a schematic view of a distributor sector at rest;
  • Figure 3; a schematic view of a distributor sector during a heating phase;
  • Figure 4; a schematic view of a dispenser sector during a cooling phase;
  • Figure 5; a perspective view of an outer platform of a dispenser sector having opening recesses; and
  • Figure 6; a perspective view of an outer platform of a dispenser sector having non-through recesses according to the invention;

La figure 1 illustre, selon une vue en coupe, un secteur de distributeur 1 installé sur une turbomachine. Au moins une aube directrice 2 est fixée sur ce secteur de distributeur 1 radialement par rapport à l'axe de révolution X dudit secteur de distributeur 1, entre une plate-forme intérieure 3 et une plate-forme extérieure 4. Sur un axe radial Y coupant orthogonalement l'axe de révolution X, une plate-forme intérieure 3 est située à une distance plus faible de cet axe X qu'une plate-forme extérieure 4.Figure 1 illustrates, in a sectional view, a distributor sector 1 installed on a turbomachine. At least one guide vane 2 is fixed on this distributor sector 1 radially with respect to the axis of revolution X of said distributor sector 1, between an inner platform 3 and an outer platform 4. On a radial axis Y orthogonally cutting the axis of revolution X, an inner platform 3 is located at a smaller distance from this axis X than an outer platform 4.

Cette aube 2 est directement exposée aux gaz chauds en provenance de la chambre de combustion. Les plates-formes 3 et 4 comportent des parties exposées directement à l'air en provenance de la chambre de combustion, notamment les surfaces 3a et 4a délimitant la veine d'air 12, et d'autres parties non exposées à cet air.This blade 2 is directly exposed to hot gases from the combustion chamber. The platforms 3 and 4 comprise parts exposed directly to the air from the combustion chamber, in particular the surfaces 3a and 4a delimiting the air stream 12, and other parts not exposed to this air.

Lors du fonctionnement de la turbomachine, selon un régime stabilisé, il existe un gradient thermique permanent sur les différentes parties d'un secteur de distributeur 1 qui impose une déformation permanente de ce secteur de distributeur 1.During operation of the turbomachine, according to a stabilized regime, there is a permanent thermal gradient on the different parts of a sector of distributor 1 which imposes a permanent deformation of this distributor sector 1.

En régime transitoire, c'est-à-dire lors d'un échauffement dû à l'augmentation du régime de la turbomachine ou d'un refroidissement dû à la diminution de ce régime, un secteur de distributeur 1 subit des déformations évolutives.Under transient conditions, that is to say during a heating due to the increase of the speed of the turbomachine or a cooling due to the decrease of this regime, a sector of distributor 1 undergoes evolutionary deformations.

Au cours d'un fonctionnement complet de la turbomachine, par exemple au cours d'un vol complet d'un aéronef comportant une telle turbomachine, ces déformations peuvent conduire à l'apparition de criques sur ce secteur de distributeur 1 et provoquer une avarie sur la turbomachine.During a complete operation of the turbomachine, for example during a complete flight of an aircraft comprising such a turbomachine, these deformations can lead to the appearance of cracks in this sector of distributor 1 and cause damage on the turbomachine.

Les figures 2, 3 et 4 représentent différentes phases de fonctionnement d'un secteur de distributeur 1.Figures 2, 3 and 4 show different operating phases of a distributor sector 1.

La figure 2 illustre schématiquement un secteur de distributeur 1 au repos, c'est-à-dire lorsque la turbomachine est à l'arrêt. Aucune contrainte thermique ni mécanique n'est exercée sur le secteur distributeur 1.FIG. 2 schematically illustrates a distributor sector 1 at rest, that is to say when the turbine engine is at a standstill. No thermal or mechanical stress is exerted on the distributor sector 1.

La figure 3 illustre schématiquement un secteur de distributeur 1 pendant une phase d'échauffement. La phase d'échauffement, la plus importante au cours d'un vol, est constatée au moment du décollage de l'aéronef. Au cours de cette phase d'échauffement, les plates-formes intérieure 3 et extérieure 4 se déforment et leurs surfaces 3a et 4a exposées à la veine d'air 12 ont tendance à devenir convexes en regard de cette veine 12. Il en résulte que les aubes 2a situées au centre du secteur de distributeur 1 subissent une compression et que les aubes 2b situées en périphérie subissent une traction.Figure 3 schematically illustrates a distributor sector 1 during a warm-up phase. The warm-up phase, the most important during a flight, is noted at the time of takeoff of the aircraft. During this heating phase, the inner 3 and outer 4 platforms deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become convex with respect to this vein 12. As a result, the blades 2a located in the center of the dispenser sector 1 undergo compression and that the blades 2b located at the periphery are subjected to traction.

La figure 4 illustre schématiquement un secteur de distributeur 1 pendant une phase de refroidissement. A l'inverse, au cours de la phase de refroidissement, les plates-formes intérieure 3 et extérieure 4 se déforment et leurs surfaces 3a et 4a exposées à la veine d'air 12 ont tendance à devenir concaves en regard de cette veine 12. Il en résulte que les aubes 2a situées au centre du secteur de distributeur 1 subissent une traction et que les aubes 2b situées en périphérie subissent une compression.Figure 4 schematically illustrates a distributor sector 1 during a cooling phase. Conversely, during the cooling phase, the inner platforms 3 and outer 4 deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become concave facing this vein 12. As a result, the blades 2a located in the center of the dispenser sector 1 are pulled and the blades 2b at the periphery undergo compression.

Les déformations des plates-formes intérieures 3 et extérieures 4 favorisent l'apparition de criques sur les secteurs de distributeur. Il est donc nécessaire de réduire la déformation des plates-formes 3 et 4 pour augmenter la durée de vie des secteurs de distributeurs et notamment des aubes 2, une aube étant généralement la pièce ayant la plus faible durée de vie sur un secteur de distributeur 1.The deformations of the inner platforms 3 and outer 4 promote the appearance of cracks on the distributor areas. It is therefore necessary to reduce the deformation of the platforms 3 and 4 to increase the service life of the valve sectors and in particular blades 2, a blade being generally the part with the shortest service life on a distributor sector 1 .

Les plates-formes 3 ou 4 d'un secteur de distributeur 1 peuvent comporter au moins un flasque 5 dit radial ou au moins un flasque 6 semi-cylindrique, comme représentés sur les figures 5 et 6. Un flasque 5 ou 6 comporte une première extrémité 5a ou 6a fixée sur la plate-forme 3 ou 4 et une seconde extrémité 5b ou 6b libre, c'est-à-dire une extrémité non fixée sur la plate-forme 3 ou 4.The platforms 3 or 4 of a distributor sector 1 may comprise at least one so-called radial flange 5 or at least one semi-cylindrical flange 6, as represented in FIGS. 5 and 6. A flange 5 or 6 comprises a first end 5a or 6a fixed on the platform 3 or 4 and a second free end 5b or 6b, that is to say a non-fixed end on the platform 3 or 4.

Un flasque radial 5 s'étend dans un plan coupant orthogonalement l'axe de révolution X du secteur de distributeur 1. Le flasque radial 5 assure un blocage axial et une étanchéité au voisinage des plates-formes 3 ou 4 du secteur de distributeur 1. Le blocage axial est la limitation de tout mouvement de translation du secteur de distributeur 1 par rapport au carter annulaire fixe 13 selon une direction parallèle à l'axe de révolution X.A radial flange 5 extends in a plane orthogonally intersecting the axis of revolution X of the distributor sector 1. The radial flange 5 provides axial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1. The axial locking is the limitation of any translational movement of the distributor sector 1 relative to the fixed annular casing 13 in a direction parallel to the axis of revolution X.

Un flasque semi-cylindrique 6 s'étend cylindriquement par rapport à l'axe de révolution X du secteur de distributeur 1. Un flasque est semi-cylindrique en ce qu'il ne s'étend que sur une portion d'un cylindre correspondant à un secteur de distributeur. Le flasque semi-cylindrique 6 assure un blocage radial et une étanchéité au voisinage des plates-formes 3 ou 4 du secteur de distributeur 1. Le blocage radial est la limitation de tout mouvement de translation du secteur de distributeur 1 selon une direction d'un axe radial Y coupant orthogonalement l'axe de révolution X.A semi-cylindrical flange 6 extends cylindrically with respect to the axis of revolution X of the distributor sector 1. A flange is semi-cylindrical in that it extends only over a portion of a cylinder corresponding to a distributor sector. The semi-cylindrical flange 6 provides a radial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1. The radial blocking is the limitation of any translational movement of the distributor sector 1 in a direction of a radial axis Y orthogonally cutting the axis of revolution X.

Au moins un moyen de blocage sur ces flasques permet le blocage tangentiel par rapport au carter annulaire fixe 13, celui-ci comportant un moyen complémentaire coopérant avec ce moyen de blocage tangentiel. Le blocage tangentiel est la limitation de tout mouvement latéral d'un secteur de distributeur 1 vers les secteurs de distributeur adjacents.At least one locking means on these flanges allows the tangential locking relative to the fixed annular casing 13, the latter comprising a complementary means cooperating with the tangential blocking means. Tangential blocking is the limitation of any lateral movement of a manifold sector 1 to the adjacent manifold sectors.

Ce moyen de blocage tangentiel peut être une entaille 7 destinée à coopérer avec un ergot complémentaire 8 sur le carter annulaire fixe 13 de la turbomachine, comme représentés sur la figure 5, ou, à l'inverse, un ergot destiné à coopérer avec une entaille complémentaire sur le carter annulaire fixe 13 de la turbomachine.This tangential blocking means may be a notch 7 intended to cooperate with a complementary lug 8 on the fixed annular casing 13 of the turbomachine, as shown in FIG. 5, or, conversely, a lug intended to cooperate with a notch complementary to the fixed annular casing 13 of the turbomachine.

Selon l'invention, au moins un flasque 5 ou 6 du secteur de distributeur 1 comporte, en outre, au moins un évidement 10 d'assouplissement libre non-débouchant. Un évidement est un enlèvement de matière dans une pièce. Il peut être débouchant ou non. On entend par « évidement libre », au sens de la présente invention, un évidement qui n'est pas destiné à coopérer avec un moyen complémentaire, par exemple pour assurer un quelconque blocage.According to the invention, at least one flange 5 or 6 of the distributor sector 1 further comprises at least one non-emerging free softening recess. A recess is a removal of material in a room. It can be opening or not. For the purposes of the present invention, the term "free recess" means a recess which is not intended for cooperate with complementary means, for example to ensure any blocking.

La figure 5 représente une plate-forme extérieure 4 de secteur de distributeur 1 comportant un flasque radial 5 et des flasques semi-cylindriques 6. Ces flasques 5 ou 6 peuvent également être présents sur une plate-forme intérieure 3. La plate-forme intérieure 3, fonctionnant selon les mêmes principes, ne sera pas décrite en détail.FIG. 5 represents an outer platform 4 of distributor sector 1 comprising a radial flange 5 and semi-cylindrical flanges 6. These flanges 5 or 6 may also be present on an inner platform 3. The inner platform 3, operating according to the same principles, will not be described in detail.

Dans cet exemple, l'évidement 9 est débouchant et se présente sous la forme d'une encoche 9. Ces encoches 9 assouplissent la plate-forme 4 du secteur de distributeur 1. Elles permettent de réduire la sensibilité des aubes aux déformations du secteur de distributeur 1 évoquées plus-haut et d'augmenter sa durée de vie. De préférence, ces encoches d'assouplissement libres 9 sont situées sur la seconde extrémité libre 5b ou 6b d'un flasque 5 ou 6. De tels évidements débouchant sont connus des documents US 3781125 et US 6210108 .In this example, the recess 9 is open and is in the form of a notch 9. These notches 9 soften the platform 4 of the distributor sector 1. They reduce the sensitivity of the blades to the deformations of the sector. Distributor 1 evoked above-high and increase its service life. Preferably, these free softening notches 9 are located on the second free end 5b or 6b of a flange 5 or 6. Such opening openings are known documents US 3781125 and US 6210108 .

La figure 6 représente une plate-forme extérieure 4 de secteur de distributeur 1, selon l'invention, comportant un flasque radial 5 et des flasques semi-cylindriques 6.FIG. 6 represents an outer platform 4 of distributor sector 1, according to the invention, comprising a radial flange 5 and semi-cylindrical flanges 6.

L'évidement 10 est non-débouchant. Ces évidements 10 consistent en des creux 10 réalisés sur les flasques 5 et 6 du secteur de distributeur 1. De tels creux 10 permettent également d'améliorer la résistance aux déformations évoquées plus-haut du secteur de distributeur 1 et d'augmenter sa durée de vie. De préférence, ces creux 10 sont situées sur la première extrémité 5a ou 6a, fixée sur la plate-forme 3 ou 4, d'un flasque 5 ou 6.The recess 10 is non-opening. These recesses 10 consist of recesses 10 made on the flanges 5 and 6 of the distributor sector 1. Such recesses 10 also make it possible to improve the resistance to the deformations referred to above of the distributor sector 1 and to increase its duration. life. Preferably, these recesses 10 are located on the first end 5a or 6a, fixed on the platform 3 or 4, of a flange 5 or 6.

Chaque secteur de distributeur 1 est fixé sur un carter annulaire 13 fixe de la turbomachine. L'assemblage des secteurs de distributeur 1 et du carter annulaire 13 constitue un distributeur de turbine.Each distributor sector 1 is fixed on a fixed annular casing 13 of the turbomachine. The assembly of the distributor sectors 1 and the annular housing 13 constitutes a turbine distributor.

Ces évidements 10 peuvent être obtenus par différentes techniques d'usinage connues en soi. De manière avantageuse, ces évidements 10 peuvent être réalisées sur des secteurs de distributeurs déjà existants. Il est donc possible d'assouplir des secteurs de distributeur déjà mis en circulation.These recesses 10 can be obtained by different machining techniques known per se. Advantageously, these recesses 10 can be realized on existing distributor sectors. It is therefore possible to relax the distributor sectors already in circulation.

La présente demande concerne également un procédé d'assouplissement d'un secteur de distributeur 1 comportant au moins une aube 2 et au moins un flasque 5 ou 6 caractérisé en qu'il consiste à usiner au moins un évidement 10 dans au moins un flasque 5 ou 6 du secteur distributeur 1.The present application also relates to a method of softening a distributor sector 1 comprising at least one blade 2 and at least one flange 5 or 6 characterized in that it consists in machining at least one recess 10 in at least one flange 5 or 6 of the distributor sector 1.

Claims (11)

Secteur de distributeur (1) de turbine de turbomachine comportant une plate-forme intérieure (3) et une plate-forme extérieure (4), au moins une aube (2) fixée entre lesdites plates-formes (3, 4), au moins une desdites plates-formes (3, 4) comportant au moins un flasque (5, 6), ayant une première extrémité (5a, 6a) fixée sur la plate-forme (3, 4) et une seconde extrémité (5b, 6b) libre, caractérisé en ce que ledit flasque (5, 6) comporte au moins un évidement (9, 10) d'assouplissement libre non-débouchant.Turbomachine turbine distributor (1) sector comprising an inner platform (3) and an outer platform (4), at least one blade (2) fixed between said platforms (3, 4), at least one blade (2) fixed between said platforms (3, 4), at least one blade (2) fixed between said platforms (3, 4), at least one blade (2) fixed between said platforms (3, 4), at least one of said platforms (3, 4) having at least one flange (5, 6) having a first end (5a, 6a) attached to the platform (3, 4) and a second end (5b, 6b) free, characterized in that said flange (5, 6) comprises at least one recess (9, 10) of non-opening free softening. Secteur de distributeur (1) selon la revendication 1 caractérisé en ce que l'évidement (10) est un creux (10).Distributor sector (1) according to claim 1 characterized in that the recess (10) is a recess (10). Secteur de distributeur (1) selon la revendication 2 caractérisé en ce que le creux (10) est situé sur la première extrémité (5a, 6a) du flasque (5, 6).Distributor sector (1) according to claim 2 characterized in that the recess (10) is located on the first end (5a, 6a) of the flange (5, 6). Secteur de distributeur (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que le flasque (5) s'étend dans un plan radial par rapport à un axe de révolution (X) dudit secteur de distributeur (1).Distributor sector (1) according to any one of the preceding claims, characterized in that the flange (5) extends in a radial plane relative to an axis of revolution (X) of said distributor sector (1). Secteur de distributeur (1) selon l'une quelconque des revendications précédentes, caractérisé en ce que le flasque (6) est semi-cylindrique par rapport à un axe de révolution (X) dudit secteur de distributeur (1).Distributor sector (1) according to any one of the preceding claims, characterized in that the flange (6) is semi-cylindrical with respect to an axis of revolution (X) of said distributor sector (1). Secteur de distributeur (1) selon l'une quelconque des revendications précédentes caractérisé en ce que qu'il comporte au moins un moyen de blocage tangentiel (7).Distributor sector (1) according to any one of the preceding claims characterized in that it comprises at least one tangential blocking means (7). Secteur de distributeur (1) selon la revendication 6 caractérisé en ce que le moyen de blocage tangentiel est une entaille (7).Distributor sector (1) according to claim 6 characterized in that the tangential blocking means is a notch (7). Distributeur de turbine comportant au moins un secteur de distributeur (1) selon l'une quelconque des revendications précédentes.A turbine distributor having at least one distributor sector (1) according to any one of the preceding claims. Turbine comportant au moins un distributeur selon la revendication 8.Turbine with at least one distributor according to claim 8. Turbomachine comportant une turbine selon la revendication 9.Turbomachine comprising a turbine according to claim 9. Procédé d'assouplissement d'un secteur de distributeur (1) de turbine de turbomachine comportant au moins une aube (2) et au moins un flasque (5, 6) caractérisé en qu'il consiste à usiner au moins un évidement non-débouchant (10) dans au moins un flasque (5, 6) du secteur distributeur (1).A method of softening a turbomachine turbine distributor sector (1) comprising at least one blade (2) and at least one flange (5, 6) characterized in that it consists in machining at least one non-opening recess (10) in at least one flange (5, 6) of the distributor sector (1).
EP06077140A 2005-12-05 2006-11-30 Improved turbomachine turbine nozzle Active EP1793093B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0512295A FR2894282A1 (en) 2005-12-05 2005-12-05 IMPROVED TURBINE MACHINE TURBINE DISPENSER

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EP1793093A2 true EP1793093A2 (en) 2007-06-06
EP1793093A3 EP1793093A3 (en) 2008-12-03
EP1793093B1 EP1793093B1 (en) 2010-03-17

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JP (1) JP4794420B2 (en)
CN (1) CN1978870B (en)
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DE (1) DE602006012915D1 (en)
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RU (1) RU2006142824A (en)

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FR3084106A1 (en) * 2018-07-23 2020-01-24 Safran Aircraft Engines LOW PRESSURE DISTRIBUTOR WITH SLIDING BLADES

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US8684683B2 (en) * 2010-11-30 2014-04-01 General Electric Company Gas turbine nozzle attachment scheme and removal/installation method
US8684689B2 (en) * 2011-01-14 2014-04-01 Hamilton Sundstrand Corporation Turbomachine shroud
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FR2928962A1 (en) * 2008-03-19 2009-09-25 Snecma Sa Distributor for low-pressure turbine of e.g. turbojet engine, of aircraft, has blades extending between two revolution walls, where one of blades comprises internal recesses for relaxing and reduction of operation constraints
FR3084106A1 (en) * 2018-07-23 2020-01-24 Safran Aircraft Engines LOW PRESSURE DISTRIBUTOR WITH SLIDING BLADES

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FR2894282A1 (en) 2007-06-08
JP2007154890A (en) 2007-06-21
CN1978870B (en) 2012-05-30
CA2569564C (en) 2013-12-24
US7780398B2 (en) 2010-08-24
JP4794420B2 (en) 2011-10-19
EP1793093A3 (en) 2008-12-03
CA2569564A1 (en) 2007-06-05
DE602006012915D1 (en) 2010-04-29
CN1978870A (en) 2007-06-13
US20070128020A1 (en) 2007-06-07
RU2006142824A (en) 2008-06-20
EP1793093B1 (en) 2010-03-17

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