EP3705684A1 - Rotor for a contra-rotating turbine of a turbine engine - Google Patents

Rotor for a contra-rotating turbine of a turbine engine Download PDF

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Publication number
EP3705684A1
EP3705684A1 EP20161551.5A EP20161551A EP3705684A1 EP 3705684 A1 EP3705684 A1 EP 3705684A1 EP 20161551 A EP20161551 A EP 20161551A EP 3705684 A1 EP3705684 A1 EP 3705684A1
Authority
EP
European Patent Office
Prior art keywords
spoiler
rotor
wing
internal
wall
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
EP20161551.5A
Other languages
German (de)
French (fr)
Other versions
EP3705684B1 (en
Inventor
Patrick Jean Laurent Sultana
Olivier Renon
Laurent Cédric ZAMAI
Clément Charles Jérémy COIFFIER
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3705684A1 publication Critical patent/EP3705684A1/en
Application granted granted Critical
Publication of EP3705684B1 publication Critical patent/EP3705684B1/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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/03—Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/44—Movement of components by counter rotation
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

Definitions

  • the present invention relates to the general field of rotors for a contra-rotating turbine of a turbomachine.
  • a counter-rotating turbine comprises in particular an internal rotor configured to rotate in a first direction of rotation and an external rotor configured to rotate in a second direction of rotation which is opposite to the first direction of rotation.
  • the internal and external rotors are movable in rotation around the longitudinal axis of the turbomachine.
  • Each of the rotors generally comprises a plurality of wheels rotatably linked to one another.
  • Each wheel comprises a disc and a vane comprising one or more blades.
  • a blading of a wheel of the outer rotor is attached internally to the corresponding disc (more commonly called a “drum”) and the blading of a wheel of the internal rotor is externally attached to the corresponding disk.
  • the wheels of the outer rotor are axially interposed between the wheels of the inner rotor.
  • the document US5307622 describes an example of mounting a vane on the disc of a wheel of the outer rotor.
  • the blading comprises several blades delimited radially by an internal platform and an external platform.
  • the vane is positioned on the disc via an upstream spoiler and a downstream spoiler made in the external platform.
  • the upstream and downstream spoilers are respectively configured to hook onto an upstream hook and a downstream hook made in a corresponding disc.
  • the blading is held in position by a screw, the head of which rests on the corresponding disc and the threaded portion cooperates with a threaded hole formed in the external platform.
  • Such an assembly does not allow any degree of freedom and thus has the advantage of immobilizing the blading during the various operating speeds of the turbomachine.
  • the screw here makes it possible to eliminate the existing assembly clearances which are the source of residual movements during operation of the turbomachine.
  • Such an assembly therefore imposes a corresponding dimensioning of the various disks, to the detriment in particular of the mass of the disks and more generally of the counter-rotating turbine.
  • the objective of the present invention is thus to provide an improved assembly making it possible to remedy the aforementioned drawbacks.
  • the invention thus proposes a rotor for a contra-rotating turbine of a turbomachine comprising a drum capable of being rotated about a longitudinal axis X and a vane mounted radially inside the drum, the drum comprising a first internal hook delimiting a first open housing, the housing having an outer wall and an inner wall, the blading comprising at least one blade and a platform external provided with a first spoiler placed inside said first housing, characterized in that the rotor comprises at least one foil attached to the first spoiler, said foil comprising an elastic inner wing and an outer wing connected to each other via a web, said outer wing being disposed radially between the first spoiler and said outer wall, said inner wing having a first support with said internal wall and a second support with the first spoiler, said inner wing being disposed in the first housing so as to exert a stress on the first spoiler at the level of said second support of so as to press said first spoiler against said outer wall via said outer wing.
  • the foil then makes it possible to press the first spoiler against the outer wall in operating speeds where the centrifugal force is not sufficient to cope with the aerodynamic forces undergone by the blading, in particular when the speed of rotation of the rotor is lower. at a predetermined threshold.
  • the foil makes it possible to damp the blading and thus to reduce the amplitude of the forces and vibrations transmitted to the drum.
  • the present invention also relates to a contra-rotating turbine for a turbomachine comprising a rotor as described above.
  • the present invention also relates to a turbomachine comprising a counter-rotating turbine as described above.
  • a contra-rotating turbine 1 of a turbomachine 2 comprising an internal rotor 3 configured to rotate in a first direction of rotation and an external rotor 4 configured to rotate in a second direction of rotation which is opposite to the first direction of rotation.
  • the internal and external rotors 3, 4 of the turbine 1 are movable in rotation about the longitudinal axis X of the turbomachine 2.
  • the turbine 1 is arranged axially directly downstream of a combustion chamber or directly downstream of a high pressure turbine which is itself arranged downstream of the combustion chamber.
  • the outer rotor 4 comprises three wheels 5 axially spaced from one another, the three wheels 5 being rotatably linked and connected to a first shaft 6.
  • the inner rotor 3 comprises three wheels 7 axially spaced from each other, the three movable wheels 7 being linked in rotation and connected to a second shaft 8 which here surrounds the first shaft 6.
  • the wheels 5 of the outer rotor 4 are interposed between the wheels 7 of the inner rotor 3.
  • a flow of exhaust gas F coming from the combustion chamber therefore passes successively through a wheel 7 of the internal rotor 3 then a wheel 5 of the external rotor 4.
  • upstream and downstream are defined with respect to the direction of flow of the flow of exhaust gas F in the turbine 1.
  • a wheel 5 of the outer rotor 4 comprises a drum 9 capable of being rotated about the longitudinal axis X and a vane 10 mounted radially inside the drum 9.
  • the drum 9 comprises a first internal hook 11 delimiting a first housing 12 open, housing 12 having an external wall 13 and an internal wall 14.
  • the blading 10 comprises at least one blade 15 and an external platform 16 provided with a first spoiler 17 placed inside the first housing 12.
  • the wheel 5 comprises at least one foil 18 attached to the first spoiler 17.
  • the foil 18 comprises an elastic internal wing 19 and an external wing 20 connected to each other via a web 21.
  • the outer wing 20 is disposed radially between the first spoiler 17 and the outer wall 13.
  • the inner wing 19 has a first support 22 with the internal wall 14 and a second support 23 with the first spoiler 17.
  • the inner wing 19 is arranged in the first housing 12 so as to exert a constraint on the first spoiler 17 at the level of the second support 23 so as to press the first spoiler 17 against the outer wall 13 via the outer wing 20.
  • the blading 10 of each of the wheels 5 of the outer rotor 4 comprises an annular row of bladed sectors disposed circumferentially end to end.
  • the blading of each of the wheels (or of one of the wheels) of the outer rotor comprises a single annular ring.
  • each bladed sector here comprises six aerodynamic blades 15 distributed in a regular manner.
  • Each of the blades 15 extends radially with respect to the axis X.
  • the blades 15 of the same bladed sector are delimited by a common external platform 16 and a common internal platform 24.
  • the external platform 16 of a bladed sector comprises a first upstream spoiler 17 (hereinafter called upstream spoiler) and a second downstream spoiler 25 (hereinafter called downstream spoiler) axially distant from one another.
  • the upstream and downstream spoilers 17, 25 here extend circumferentially in the form of a ring sector.
  • the upstream and downstream spoilers 17, 25 here extend circumferentially over the total length of the sector.
  • the upstream and downstream spoilers 17, 25 are each oriented axially from downstream to upstream from a radially outer end of a flange 26, each flange 26 projecting radially outward from a plate 27 of the outer platform 16 .
  • the upstream and downstream spoilers could for example be oriented axially from upstream to downstream.
  • the upstream and downstream spoilers extend circumferentially in the form of a ring.
  • Each of the upstream and downstream spoilers 17, 25 has a substantially rectangular profile in section and is thus delimited by an outer face 28 and an inner face 29 connected to each other by an upstream face 30.
  • the outer and inner faces 28 , 29 are coaxial, the upstream face 30 being flat.
  • the bladed sector is obtained in one piece, and in other words the internal and external platforms 16, 24 are integral with the blades 15.
  • the bladed sector could be obtained by assembling different sub-assemblies.
  • a spoiler could be integral with a flange so as to form a sub-assembly attached to the plate of the external platform.
  • the drum 9 of a wheel 5 of the outer rotor 4 comprises a first upstream internal hook 11 (hereinafter referred to as the upstream hook) and a second downstream internal hook 31 (hereinafter referred to as the hook downstream) axially distant from each other.
  • the upstream and downstream hooks 11, 31 respectively form a first upstream housing 12 (hereinafter referred to as upstream housing) and a second downstream housing 32 (hereinafter referred to as downstream housing).
  • the upstream and downstream hooks 11, 31 are annular. Each of the hooks 11, 31 has in section a substantially “C” profile.
  • the housings 12, 32 are open downstream.
  • Each of the upstream and downstream housings 12, 32 is thus delimited by an outer wall 13 and an inner wall 14 connected to each other by an upstream wall 33.
  • the outer and inner walls 13, 14 are more precisely coaxial, the upstream wall 33 being flat.
  • each bladed sector may comprise a single foil in the form of a ring sector, or several foils each in the form of a ring sector and distributed circumferentially in a regular manner.
  • the blading of a wheel of the outer rotor comprises a single annular ring gear
  • the blading may comprise a single foil in the form of a ring, or several foils each in the form of a ring sector and distributed circumferentially in a regular manner.
  • a foil 18 may be annular or a ring sector.
  • a foil 18 has in section a substantially “C” or “U” -shaped profile, the opening of which opens downstream.
  • the inner and outer wings 19, 20 are thus located opposite one another.
  • the outer wing 20 can be annular or a ring sector.
  • the core 21 is flat and may be annular or a ring sector.
  • the internal wing 19 has a corrugated profile in section. More specifically, the inner flange 19 comprises a first concave section 34 connected directly to the web 21 and a second convex section 35 connected to the first section 34 via an inflection point I.
  • the concavity / convexity of the inner flange 19 is determined in the radial direction oriented from the outside to the inside.
  • the second section 35 has a greater curvature than the first section 34. With respect to the first section 34, the second section 35 is radially offset in the direction of the outer wing 20.
  • the point of inflection I is located radially between the first press 22 and the second press 23.
  • the first support 22 between the internal wing 19 and the internal wall 14 is located at the level of the first section 34.
  • the second support 23 between the internal wing 19 and the upstream spoiler 17 is located at the level of the second section 35.
  • the first and second supports 22, 23 are linear and annular.
  • the first support 22 is disposed at a radially internal end of the foil 18.
  • the second support 23 is located radially substantially at mid-height of the web 21.
  • the inner wing 19 elastically deforms between a resting state in which no external force is applied to the clicker and a loaded state in which opposing external forces are applied to the inner and outer wings 19, 20 of the foil 18 so as to bring them closer to each other.
  • the foil 18 passes from a state at rest to a loaded state, during the introduction of the foil 18 into the upstream housing 12.
  • the internal flange 19 exerts a prestressing force (or preload) on the upstream spoiler 17 at the second fulcrum 23, this prestressing force being oriented radially from the inside to the outside.
  • the preload force is directly related to the restoring force exerted by the inner flange 19 on the internal wall 14 at the level of the first support 22, this restoring force being oriented radially from the outside to the inside.
  • a click is made of a heat resistant material, for example a cobalt and / or nickel based alloy.
  • each sector is placed in position on the drum 9 by respectively introducing the upstream and downstream spoilers 17, 25 into the upstream and downstream housings 12, 32 of the drum 9, the foil (s) 18 being previously reported on the upstream spoiler 17 of the corresponding sector.
  • the outer wing 20 is located radially between the outer face 28 and the outer wall 13.
  • the outer flange 20 is pressed against the outer wall 13 under the action of the upstream spoiler 17 which is itself subjected to the prestressing force generated by the elastic deformation of the inner flange 19 and / or to the centrifugal force.
  • the core 21 is located axially between the upstream wall 33 and the upstream face 30, the core 21 possibly being flush with the upstream face 30 or resting on the upstream face 30.
  • the internal wing 19 is located radially between the internal face 29 and the internal wall 14.
  • the internal wing 19 exerts a prestressing force on the upstream spoiler 17 at the level of the second support 23 so as to press the upstream spoiler 17 against the outer wall 13 via the outer flange 20.
  • the preload force is predetermined so as to press the upstream spoiler 17 against the outer wall 13 in operating speeds where the centrifugal force is not sufficient to do so (namely when the aerodynamic forces exerted on the blade are greater than centrifugal force), in particular when the speed of rotation of the outer rotor 4 is below a predetermined threshold.
  • the foils 18 thus make it possible to immobilize the sectors, and in other words to avoid residual movements (such as the pivoting of the sectors), in particular when the speed of rotation of the outer rotor 4 is below the predetermined threshold.
  • the prestressing force is predetermined so as to damp the bladed sectors and thus reduce the amplitude of the forces and vibrations transmitted to the drum 9.
  • the foil (s) 18 thus form a damper for the corresponding sector.
  • the downstream spoiler 25 is mounted in the downstream housing 32 with radial play.
  • the internal face 29 is flush with the internal wall 14 or rests on the internal wall 14 and the external face 28 is flush with the external wall 13 or rests on the external wall 13 .
  • each sector is held axially in position by at least one stop ring 36 housed in part in an annular groove 37 formed in the drum 9.
  • the stop ring 36 is partly housed in the groove 37 and partly in axial bearing against a downstream surface of the flange 26 associated with the downstream spoiler 25.
  • each bladed sector comprises a single click, in other words the foil 18 extends circumferentially over the total length of the upstream spoiler 17.
  • each bladed sector comprises several foils 18 distributed circumferentially in a regular manner.
  • each foil 18 extends only over a circumferential portion of the upstream spoiler 17.
  • each sector can then comprise between two and ten foils 18.
  • the foil 18 is clipped onto the upstream spoiler 17.
  • the inner flange 19 is elastically deformed so that the inner flange 19 exerts a holding force on the upstream spoiler 17 at the second fulcrum 23, this holding force being oriented radially from the inside to the outside.
  • This force of maintenance keeps the foil 18 on the sector when mounting the sector on the drum 9.
  • the upstream spoiler 17 comprises a protuberance 38 projecting from its internal face 29.
  • the protuberance 38 is disposed axially between the core 21 and the second support 23.
  • the internal wing 19 is elastically deformed so as to increase the distance between the inner flange 19 and the outer flange 20, and thus allow the passage of the protuberance 38. After mounting the foil 18, the foil 18 is thus blocked. axially by the protuberance 38.
  • the protuberance 38 has a rounded profile in section, in order to facilitate the mounting of the foil 18 on the upstream spoiler 17.

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

Abstract

Rotor (4) pour une turbine contrarotative (1) comprenant un tambour (9) et un aubage (10) monté à l'intérieur, ledit tambour (9) comprenant un crochet (11) délimitant un logement (12) présentant une paroi externe et une paroi interne, ledit aubage (10) comprenant une pale (15) et une plateforme externe (16) pourvue d'un becquet (17) placé à l'intérieur dudit logement (12),caractérisé en ce que le rotor (4) comprend un clinquant (18) comprenant une aile interne élastique et une aile externe, ladite aile externe étant disposée radialement entre ledit becquet (17) et ladite paroi externe, ladite aile interne présentant un premier appui avec ladite paroi interne et un second appui avec ledit becquet (17), ladite aile interne étant disposée dans le logement (12) de sorte à exercer une contrainte sur ledit becquet (17) de manière à plaquer ledit becquet (17) contre ladite paroi externe via ladite aile externe.Rotor (4) for a counter-rotating turbine (1) comprising a drum (9) and a vane (10) mounted inside, said drum (9) comprising a hook (11) delimiting a housing (12) having an outer wall and an internal wall, said vane (10) comprising a blade (15) and an external platform (16) provided with a spoiler (17) placed inside said housing (12), characterized in that the rotor (4 ) comprises a foil (18) comprising an elastic internal wing and an external wing, said external wing being disposed radially between said spoiler (17) and said external wall, said internal wing having a first support with said internal wall and a second support with said spoiler (17), said inner wing being arranged in the housing (12) so as to exert a stress on said spoiler (17) so as to press said spoiler (17) against said outer wall via said outer wing.

Description

Domaine technique de l'inventionTechnical field of the invention

La présente invention se rapporte au domaine général des rotors pour une turbine contrarotative de turbomachine.The present invention relates to the general field of rotors for a contra-rotating turbine of a turbomachine.

Arrière-plan techniqueTechnical background

Il est connu du document FR-A1-2942273 au nom de la demanderesse d'implanter une turbine contrarotative au sein d'une turbomachine. Une telle turbine contrarotative comprend notamment un rotor interne configuré pour tourner dans un premier sens de rotation et un rotor externe configuré pour tourner dans un second sens de rotation qui est opposé au premier sens de rotation. Les rotors interne et externe sont mobiles en rotation autour de l'axe longitudinal de la turbomachine.It is known from the document FR-A1-2942273 in the name of the applicant to install a counter-rotating turbine within a turbomachine. Such a counter-rotating turbine comprises in particular an internal rotor configured to rotate in a first direction of rotation and an external rotor configured to rotate in a second direction of rotation which is opposite to the first direction of rotation. The internal and external rotors are movable in rotation around the longitudinal axis of the turbomachine.

Chacun des rotors comprend généralement une pluralité de roues liées en rotation les unes aux autres. Chaque roue comprend un disque et un aubage comportant une ou plusieurs pales. Par définition, un aubage d'une roue du rotor externe est rapporté intérieurement sur le disque correspondant (plus communément appelé « tambour ») et l'aubage d'une roue du rotor interne est rapporté extérieurement sur le disque correspondant. Les roues du rotor externe sont axialement intercalées entre les roues du rotor interne.Each of the rotors generally comprises a plurality of wheels rotatably linked to one another. Each wheel comprises a disc and a vane comprising one or more blades. By definition, a blading of a wheel of the outer rotor is attached internally to the corresponding disc (more commonly called a “drum”) and the blading of a wheel of the internal rotor is externally attached to the corresponding disk. The wheels of the outer rotor are axially interposed between the wheels of the inner rotor.

On s'intéressera plus particulièrement au rotor externe dans la suite de la description.We will focus more particularly on the outer rotor in the remainder of the description.

Le document US5307622 décrit un exemple de montage d'un aubage sur le disque d'une roue du rotor externe. L'aubage comprend plusieurs pales délimitées radialement par une plateforme interne et une plateforme externe. L'aubage est mis en position sur le disque via un becquet amont et un becquet aval pratiqués dans la plateforme externe. Les becquets amont et aval sont respectivement configurés pour s'accrocher à un crochet amont et un crochet aval pratiqués dans un disque correspondant. L'aubage est maintenu en position par une vis dont la tête est en appui sur le disque correspondant et la portion filetée coopère avec un trou taraudé formé dans la plateforme externe.The document US5307622 describes an example of mounting a vane on the disc of a wheel of the outer rotor. The blading comprises several blades delimited radially by an internal platform and an external platform. The vane is positioned on the disc via an upstream spoiler and a downstream spoiler made in the external platform. The upstream and downstream spoilers are respectively configured to hook onto an upstream hook and a downstream hook made in a corresponding disc. The blading is held in position by a screw, the head of which rests on the corresponding disc and the threaded portion cooperates with a threaded hole formed in the external platform.

Un tel montage n'autorise aucun degré de liberté et présente ainsi l'avantage d'immobiliser l'aubage lors des différents régimes de fonctionnement de la turbomachine. En effet, la vis permet ici de supprimer les jeux de montage existants qui sont à l'origine de mouvements résiduels lors du fonctionnement de la turbomachine.Such an assembly does not allow any degree of freedom and thus has the advantage of immobilizing the blading during the various operating speeds of the turbomachine. Indeed, the screw here makes it possible to eliminate the existing assembly clearances which are the source of residual movements during operation of the turbomachine.

Toutefois, un tel montage sollicite significativement les disques des différentes roues du rotor externe. En effet, les forces aérodynamique et centrifuge s'exerçant sur l'aubage sont reprises mécaniquement par le disque. En outre, les sollicitations vibratoires s'exerçant sur l'aubage sont également reprises par le disque sans amortissement préalable. Ces sollicitations vibratoires sont maximales lorsque l'aubage est en résonnance.However, such an arrangement significantly stresses the discs of the various wheels of the outer rotor. In fact, the aerodynamic and centrifugal forces exerted on the blading are taken up mechanically by the disc. In addition, the vibratory stresses exerted on the blading are also taken up by the disc without prior damping. These vibratory stresses are maximum when the blading is in resonance.

Un tel montage impose donc un dimensionnement en conséquence des différents disques, au détriment notamment de la masse des disques et plus généralement de la turbine contrarotative.Such an assembly therefore imposes a corresponding dimensioning of the various disks, to the detriment in particular of the mass of the disks and more generally of the counter-rotating turbine.

L'objectif de la présente invention est ainsi de proposer un montage amélioré permettant de remédier aux inconvénients précités.The objective of the present invention is thus to provide an improved assembly making it possible to remedy the aforementioned drawbacks.

Résumé de l'inventionSummary of the invention

L'invention propose ainsi un rotor pour une turbine contrarotative de turbomachine comprenant un tambour apte à être mis en rotation autour d'un axe longitudinal X et un aubage monté radialement à l'intérieur du tambour, le tambour comprenant un premier crochet interne délimitant un premier logement ouvert, le logement présentant une paroi externe et une paroi interne, l'aubage comprenant au moins une pale et une plateforme externe pourvue d'un premier becquet placé à l'intérieur dudit premier logement,
caractérisé en ce que le rotor comprend au moins un clinquant rapporté sur le premier becquet, ledit clinquant comprenant une aile interne élastique et une aile externe reliées l'une à l'autre via une âme, ladite aile externe étant disposée radialement entre le premier becquet et ladite paroi externe, ladite aile interne présentant un premier appui avec ladite paroi interne et un second appui avec le premier becquet, ladite aile interne étant disposée dans le premier logement de sorte à exercer une contrainte sur le premier becquet au niveau dudit second appui de manière à plaquer ledit premier becquet contre ladite paroi externe via ladite aile externe.The invention thus proposes a rotor for a contra-rotating turbine of a turbomachine comprising a drum capable of being rotated about a longitudinal axis X and a vane mounted radially inside the drum, the drum comprising a first internal hook delimiting a first open housing, the housing having an outer wall and an inner wall, the blading comprising at least one blade and a platform external provided with a first spoiler placed inside said first housing,
characterized in that the rotor comprises at least one foil attached to the first spoiler, said foil comprising an elastic inner wing and an outer wing connected to each other via a web, said outer wing being disposed radially between the first spoiler and said outer wall, said inner wing having a first support with said internal wall and a second support with the first spoiler, said inner wing being disposed in the first housing so as to exert a stress on the first spoiler at the level of said second support of so as to press said first spoiler against said outer wall via said outer wing.

Le clinquant permet alors de plaquer le premier becquet contre la paroi externe dans les régimes de fonctionnement où la force centrifuge n'est pas suffisante pour le faire face aux efforts aérodynamiques subis par l'aubage, notamment lorsque la vitesse de rotation du rotor est inférieur à un seuil prédéterminé.The foil then makes it possible to press the first spoiler against the outer wall in operating speeds where the centrifugal force is not sufficient to cope with the aerodynamic forces undergone by the blading, in particular when the speed of rotation of the rotor is lower. at a predetermined threshold.

En outre, le clinquant permet d'amortir l'aubage et ainsi de réduire l'amplitude des efforts et des vibrations transmis au tambour.In addition, the foil makes it possible to damp the blading and thus to reduce the amplitude of the forces and vibrations transmitted to the drum.

Un tel montage réduit ainsi de manière significative l'usure, au bénéfice de la durée de vie du rotor.Such an assembly thus significantly reduces wear, to the benefit of the service life of the rotor.

Le rotor selon l'invention peut comprendre une ou plusieurs des caractéristiques et/ou étapes suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • ladite plateforme externe de l'aubage comprend un second becquet distant dudit premier becquet et disposé axialement en aval dudit premier becquet, ledit second becquet étant placé à l'intérieur d'un second logement délimité par un second crochet interne du tambour ;
  • les premier et second becquets sont orientés chacun axialement de l'aval vers l'amont, lesdits premier et second logements étant ouverts axialement vers l'aval ;
  • le clinquant est clippé sur ledit premier becquet ;
  • le premier becquet comprend une protubérance en saillie depuis une face interne, ladite protubérance étant axialement disposée entre ladite âme et ledit second appui ;
  • le clinquant est un anneau ou un secteur d'anneau ;
  • ladite aile interne comprend un premier tronçon courbe connecté directement à ladite âme et un second tronçon courbe connecté audit premier tronçon via un point d'inflexion I, lesdits premier et second appuis étant disposés respectivement au niveau dudit premier tronçon et dudit second tronçon ;
  • ledit premier tronçon est concave et ledit second tronçon est convexe.
The rotor according to the invention can comprise one or more of the following characteristics and / or steps, taken in isolation from one another or in combination with one another:
  • said outer platform of the blade comprises a second spoiler remote from said first spoiler and disposed axially downstream of said first spoiler, said second spoiler being placed inside a second housing delimited by a second internal hook of the drum;
  • the first and second spoilers are each oriented axially from downstream to upstream, said first and second housings being open axially downstream;
  • the foil is clipped onto said first spoiler;
  • the first spoiler comprises a protrusion projecting from an internal face, said protuberance being axially disposed between said web and said second support;
  • the foil is a ring or ring sector;
  • said internal wing comprises a first curved section connected directly to said web and a second curved section connected to said first section via an inflection point I, said first and second supports being respectively arranged at said first section and said second section;
  • said first section is concave and said second section is convex.

La présente invention concerne encore une turbine contrarotative de turbomachine comprenant un rotor tel que décrit précédemment.The present invention also relates to a contra-rotating turbine for a turbomachine comprising a rotor as described above.

La présente invention concerne également une turbomachine comprenant une turbine contrarotative telle que décrite précédemment.The present invention also relates to a turbomachine comprising a counter-rotating turbine as described above.

Brève description des figuresBrief description of the figures

L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront plus clairement à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • [Fig.1] la figure 1 est une vue schématique en demi-coupe axiale d'une turbine contrarotative comprenant un rotor interne et un rotor externe contrarotatifs ;
  • [Fig.2] la figure 2 est une vue de détail schématique en demi-coupe axiale illustrant l'assemblage d'un secteur aubagé sur un tambour du rotor externe ;
  • [Fig.3] la figure 3 est une vue de détail en perspective illustrant l'assemblage d'un becquet amont du secteur aubagé sur le tambour via un clinquant ;
  • [Fig.4] la figure 4 est une vue de détail en demi-coupe axiale illustrant l'assemblage du becquet amont sur le tambour via le clinquant ;
  • [Fig.5] la figure 5 est une vue éclatée en perspective du secteur aubagé et du clinquant illustrés sur les figures 2 à 4 ;
  • [Fig.6] la figure 6 est une vue éclatée en perspective illustrant une première variante de réalisation ;
  • [Fig.7] la figure 7 est une vue de détail en perspective illustrant une seconde variante de réalisation.
The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:
  • [ Fig. 1 ] the figure 1 is a schematic view in axial half-section of a counter-rotating turbine comprising an inner rotor and a counter-rotating outer rotor;
  • [ Fig. 2 ] the figure 2 is a schematic detail view in axial half-section illustrating the assembly of a bladed sector on a drum of the outer rotor;
  • [ Fig. 3 ] the figure 3 is a detail perspective view illustrating the assembly of an upstream spoiler of the bladed sector on the drum via a foil;
  • [ Fig. 4 ] the figure 4 is a detail view in axial half-section illustrating the assembly of the upstream spoiler on the drum via the foil;
  • [ Fig. 5 ] the figure 5 is an exploded perspective view of the bladed sector and foil illustrated on the figures 2 to 4 ;
  • [ Fig. 6 ] the figure 6 is an exploded perspective view illustrating a first variant embodiment;
  • [ Fig. 7 ] the figure 7 is a detail perspective view illustrating a second variant embodiment.

Description détaillée de l'inventionDetailed description of the invention

Sur la figure 1 est représentée schématiquement une turbine contrarotative 1 de turbomachine 2 comprenant un rotor interne 3 configuré pour tourner dans un premier sens de rotation et un rotor externe 4 configuré pour tourner dans un second sens de rotation qui est opposé au premier sens de rotation. Les rotors interne et externe 3, 4 de la turbine 1 sont mobiles en rotation autour de l'axe longitudinal X de la turbomachine 2.On the figure 1 is schematically shown a contra-rotating turbine 1 of a turbomachine 2 comprising an internal rotor 3 configured to rotate in a first direction of rotation and an external rotor 4 configured to rotate in a second direction of rotation which is opposite to the first direction of rotation. The internal and external rotors 3, 4 of the turbine 1 are movable in rotation about the longitudinal axis X of the turbomachine 2.

Par convention dans la présente demande, on entend par « axial » ou « axialement » toute direction parallèle à l'axe X, et par « radial » ou « radialement » toute direction perpendiculaire à l'axe X. De même, dans la présente demande, les termes « interne », « externe », « intérieur » ou « extérieur » sont définis par rapport à l'axe longitudinal X de la turbomachine 2.By convention in the present application, by “axial” or “axially” is meant any direction parallel to the X axis, and by “radial” or “radially” any direction perpendicular to the X axis. Likewise, in the present invention Request, the terms “internal”, “external”, “interior” or “exterior” are defined with respect to the longitudinal axis X of the turbomachine 2.

La turbine 1 est disposée axialement directement en aval d'une chambre de combustion ou directement en aval d'une turbine haute pression qui est elle-même disposée en aval de la chambre de combustion.The turbine 1 is arranged axially directly downstream of a combustion chamber or directly downstream of a high pressure turbine which is itself arranged downstream of the combustion chamber.

Tel qu'illustré sur la figure 1, le rotor externe 4 comprend trois roues 5 espacées axialement les unes des autres, les trois roues 5 étant liées en rotation et connectées à un premier arbre 6. De la même manière que le rotor externe 4, le rotor interne 3 comprend trois roues 7 espacés axialement les unes des autres, les trois roues 7 mobiles étant liées en rotation et connectées à un second arbre 8 qui entoure ici le premier arbre 6. Les roues 5 du rotor externe 4 sont intercalées entre les roues 7 du rotor interne 3.As shown on figure 1 , the outer rotor 4 comprises three wheels 5 axially spaced from one another, the three wheels 5 being rotatably linked and connected to a first shaft 6. In the same way as the outer rotor 4, the inner rotor 3 comprises three wheels 7 axially spaced from each other, the three movable wheels 7 being linked in rotation and connected to a second shaft 8 which here surrounds the first shaft 6. The wheels 5 of the outer rotor 4 are interposed between the wheels 7 of the inner rotor 3.

Un flux de gaz d'échappement F en provenance de la chambre de combustion traverse donc successivement une roue 7 du rotor interne 3 puis une roue 5 du rotor externe 4.A flow of exhaust gas F coming from the combustion chamber therefore passes successively through a wheel 7 of the internal rotor 3 then a wheel 5 of the external rotor 4.

Dans la présente demande, les termes « amont » et « aval » sont définis par rapport au sens d'écoulement du flux de gaz d'échappement F dans la turbine 1.In the present application, the terms “upstream” and “downstream” are defined with respect to the direction of flow of the flow of exhaust gas F in the turbine 1.

On s'intéressa plus particulièrement aux roues 5 du rotor externe 4 dans la suite de la description.We will focus more particularly on the wheels 5 of the outer rotor 4 in the remainder of the description.

Une roue 5 du rotor externe 4 comprend un tambour 9 apte à être mis en rotation autour de l'axe longitudinal X et un aubage 10 monté radialement à l'intérieur du tambour 9. Le tambour 9 comprend un premier crochet interne 11 délimitant un premier logement 12 ouvert, le logement 12 présentant une paroi externe 13 et une paroi interne 14. L'aubage 10 comprend au moins une pale 15 et une plateforme externe 16 pourvue d'un premier becquet 17 placé à l'intérieur du premier logement 12.A wheel 5 of the outer rotor 4 comprises a drum 9 capable of being rotated about the longitudinal axis X and a vane 10 mounted radially inside the drum 9. The drum 9 comprises a first internal hook 11 delimiting a first housing 12 open, housing 12 having an external wall 13 and an internal wall 14. The blading 10 comprises at least one blade 15 and an external platform 16 provided with a first spoiler 17 placed inside the first housing 12.

Selon l'invention, la roue 5 comprend au moins un clinquant 18 rapporté sur le premier becquet 17. Le clinquant 18 comprend une aile interne élastique 19 et une aile externe 20 reliées l'une à l'autre via une âme 21. L'aile externe 20 est disposée radialement entre le premier becquet 17 et la paroi externe 13. L'aile interne 19 présente un premier appui 22 avec la paroi interne 14 et un second appui 23 avec le premier becquet 17. L'aile interne 19 est disposée dans le premier logement 12 de sorte à exercer une contrainte sur le premier becquet 17 au niveau du second appui 23 de manière à plaquer le premier becquet 17 contre la paroi externe 13 via l'aile externe 20.According to the invention, the wheel 5 comprises at least one foil 18 attached to the first spoiler 17. The foil 18 comprises an elastic internal wing 19 and an external wing 20 connected to each other via a web 21. The outer wing 20 is disposed radially between the first spoiler 17 and the outer wall 13. The inner wing 19 has a first support 22 with the internal wall 14 and a second support 23 with the first spoiler 17. The inner wing 19 is arranged in the first housing 12 so as to exert a constraint on the first spoiler 17 at the level of the second support 23 so as to press the first spoiler 17 against the outer wall 13 via the outer wing 20.

Selon les modes de réalisation illustrés sur les figures, l'aubage 10 de chacune des roues 5 du rotor externe 4 comprend une rangée annulaire de secteurs aubagés disposés circonférentiellement bout à bout.According to the embodiments illustrated in the figures, the blading 10 of each of the wheels 5 of the outer rotor 4 comprises an annular row of bladed sectors disposed circumferentially end to end.

En variante, l'aubage de chacune des roues (ou de l'une des roues) du rotor externe comprend une unique couronne annulaire.As a variant, the blading of each of the wheels (or of one of the wheels) of the outer rotor comprises a single annular ring.

Plus précisément, tel qu'illustré sur les figures 5 et 6, chaque secteur aubagé comprend ici six pales aérodynamiques 15 réparties de manière régulière. Chacune des pales 15 s'étend radialement par rapport à l'axe X. Les pales 15 d'un même secteur aubagé sont délimitées par une plateforme externe commune 16 et une plateforme interne commune 24.More precisely, as illustrated on figures 5 and 6 , each bladed sector here comprises six aerodynamic blades 15 distributed in a regular manner. Each of the blades 15 extends radially with respect to the axis X. The blades 15 of the same bladed sector are delimited by a common external platform 16 and a common internal platform 24.

La plateforme externe 16 d'un secteur aubagé comprend un premier becquet amont 17 (ci-après dénommé becquet amont) et un second becquet aval 25 (ci-après dénommé becquet aval) distants axialement l'un de l'autre. Les becquets amont et aval 17, 25 s'étendent ici circonférentiellement sous la forme d'un secteur d'anneau. Les becquets amont et aval 17, 25 s'étendent ici circonférentiellement sur la longueur totale du secteur. Les becquets amont et aval 17, 25 sont chacun orientés axialement de l'aval vers l'amont depuis une extrémité radialement externe d'une collerette 26, chaque collerette 26 faisant saillie radialement vers l'extérieur depuis un plateau 27 de la plateforme externe 16.The external platform 16 of a bladed sector comprises a first upstream spoiler 17 (hereinafter called upstream spoiler) and a second downstream spoiler 25 (hereinafter called downstream spoiler) axially distant from one another. The upstream and downstream spoilers 17, 25 here extend circumferentially in the form of a ring sector. The upstream and downstream spoilers 17, 25 here extend circumferentially over the total length of the sector. The upstream and downstream spoilers 17, 25 are each oriented axially from downstream to upstream from a radially outer end of a flange 26, each flange 26 projecting radially outward from a plate 27 of the outer platform 16 .

En variante, les becquets amont et aval pourraient être par exemple orientés axialement de l'amont vers l'aval.As a variant, the upstream and downstream spoilers could for example be oriented axially from upstream to downstream.

Dans le cas où l'aubage comprend une unique couronne annulaire, les becquets amont et aval s'étendent circonférentiellement sous la forme d'un d'anneau.In the case where the blading comprises a single annular ring, the upstream and downstream spoilers extend circumferentially in the form of a ring.

Chacun des becquets amont et aval 17, 25 présente en section un profil sensiblement rectangulaire et est ainsi délimité par une face externe 28 et une face interne 29 reliées l'une à l'autre par une face amont 30. Les faces externe et interne 28, 29 sont coaxiales, la face amont 30 étant plane.Each of the upstream and downstream spoilers 17, 25 has a substantially rectangular profile in section and is thus delimited by an outer face 28 and an inner face 29 connected to each other by an upstream face 30. The outer and inner faces 28 , 29 are coaxial, the upstream face 30 being flat.

Selon les modes de réalisation illustrés sur figures, le secteur aubagé est obtenu d'un seul tenant, et autrement dit les plateformes interne et externe 16, 24 sont venues de matière avec les pales 15.According to the embodiments illustrated in the figures, the bladed sector is obtained in one piece, and in other words the internal and external platforms 16, 24 are integral with the blades 15.

En variante, le secteur aubagé pourrait être obtenu via l'assemblage de différents sous-ensembles. A titre d'exemple, un becquet pourrait être venu de matière avec une collerette de manière à former un sous-ensemble rapporté sur le plateau de la plateforme externe.As a variant, the bladed sector could be obtained by assembling different sub-assemblies. By way of example, a spoiler could be integral with a flange so as to form a sub-assembly attached to the plate of the external platform.

Selon les modes de réalisation illustrés sur les figures, le tambour 9 d'une roue 5 du rotor externe 4 comprend un premier crochet interne amont 11 (ci-après dénommé crochet amont) et un second crochet interne aval 31 (ci-après dénommé crochet aval) distants axialement l'un de l'autre. Les crochets amont et aval 11, 31 forment respectivement un premier logement amont 12 (ci-après dénommé logement amont) et un second logement aval 32 (ci-après dénommé logement aval).According to the embodiments illustrated in the figures, the drum 9 of a wheel 5 of the outer rotor 4 comprises a first upstream internal hook 11 (hereinafter referred to as the upstream hook) and a second downstream internal hook 31 (hereinafter referred to as the hook downstream) axially distant from each other. The upstream and downstream hooks 11, 31 respectively form a first upstream housing 12 (hereinafter referred to as upstream housing) and a second downstream housing 32 (hereinafter referred to as downstream housing).

Plus précisément, les crochets amont et aval 11, 31 sont annulaires. Chacun des crochets 11, 31 présente en section un profil sensiblement en « C ». Les logements 12, 32 sont ouverts vers l'aval. Chacun des logements amont et aval 12, 32 est ainsi délimité par une paroi externe 13 et une paroi interne 14 reliées l'une à l'autre par une paroi amont 33. Les parois externe et interne 13, 14 sont plus précisément coaxiales, la paroi amont 33 étant plane.More precisely, the upstream and downstream hooks 11, 31 are annular. Each of the hooks 11, 31 has in section a substantially “C” profile. The housings 12, 32 are open downstream. Each of the upstream and downstream housings 12, 32 is thus delimited by an outer wall 13 and an inner wall 14 connected to each other by an upstream wall 33. The outer and inner walls 13, 14 are more precisely coaxial, the upstream wall 33 being flat.

Dans le cas où l'aubage d'une roue du rotor externe comprend une rangée annulaire de secteurs aubagés disposés circonférentiellement bout à bout, chaque secteur aubagé peut comprendre un unique clinquant se présentant sous la forme d'un secteur d'anneau, ou plusieurs clinquants se présentant chacun sous la forme d'un secteur d'anneau et répartis circonférentiellement de manière régulière.In the case where the blading of a wheel of the outer rotor comprises an annular row of bladed sectors disposed circumferentially end to end, each bladed sector may comprise a single foil in the form of a ring sector, or several foils each in the form of a ring sector and distributed circumferentially in a regular manner.

Dans le cas où l'aubage d'une roue du rotor externe comprend une unique couronne annulaire, l'aubage peut comprendre un unique clinquant se présentant sous la forme d'un anneau, ou plusieurs clinquants se présentant chacun sous la forme d'un secteur d'anneau et répartis circonférentiellement de manière régulière.In the case where the blading of a wheel of the outer rotor comprises a single annular ring gear, the blading may comprise a single foil in the form of a ring, or several foils each in the form of a ring sector and distributed circumferentially in a regular manner.

Selon les modes de réalisation illustrés sur les figures, un clinquant 18 peut être annulaire ou un secteur d'anneau. Un clinquant 18 présente en section un profil sensiblement en « C » ou en « U » dont l'ouverture débouche vers l'aval. Les ailes interne et externe 19, 20 se trouvent ainsi en regard l'une de l'autre.According to the embodiments illustrated in the figures, a foil 18 may be annular or a ring sector. A foil 18 has in section a substantially “C” or “U” -shaped profile, the opening of which opens downstream. The inner and outer wings 19, 20 are thus located opposite one another.

Plus précisément, l'aile externe 20 peut être annulaire ou un secteur d'anneau. L'âme 21 est plane et peut être annulaire ou un secteur d'anneau. L'aile interne 19 présente en section un profil ondulée. Plus précisément, l'aile interne 19 comprend un premier tronçon concave 34 connecté directement à l'âme 21 et un second tronçon convexe 35 connecté au premier tronçon 34 via un point d'inflexion I. La concavité/convexité de l'aile interne 19 est déterminée selon la direction radiale orientée de l'extérieur vers l'intérieur. Le second tronçon 35 présente une courbure plus grande que le premier tronçon 34. Par rapport au premier tronçon 34, le second tronçon 35 est décalé radialement en direction de l'aile externe 20. Le point d'inflexion I se trouve radialement entre le premier appui 22 et le second appui 23.More precisely, the outer wing 20 can be annular or a ring sector. The core 21 is flat and may be annular or a ring sector. The internal wing 19 has a corrugated profile in section. More specifically, the inner flange 19 comprises a first concave section 34 connected directly to the web 21 and a second convex section 35 connected to the first section 34 via an inflection point I. The concavity / convexity of the inner flange 19 is determined in the radial direction oriented from the outside to the inside. The second section 35 has a greater curvature than the first section 34. With respect to the first section 34, the second section 35 is radially offset in the direction of the outer wing 20. The point of inflection I is located radially between the first press 22 and the second press 23.

Le premier appui 22 entre l'aile interne 19 et la paroi interne 14 se trouve au niveau du premier tronçon 34. Le second appui 23 entre l'aile interne 19 et le becquet amont 17 se trouve au niveau du second tronçon 35. Les premier et second appuis 22, 23 sont linéaires et annulaires. Le premier appui 22 est disposé à une extrémité radialement interne du clinquant 18. Le second appui 23 se trouve radialement sensiblement à mi-hauteur de l'âme 21.The first support 22 between the internal wing 19 and the internal wall 14 is located at the level of the first section 34. The second support 23 between the internal wing 19 and the upstream spoiler 17 is located at the level of the second section 35. The first and second supports 22, 23 are linear and annular. The first support 22 is disposed at a radially internal end of the foil 18. The second support 23 is located radially substantially at mid-height of the web 21.

L'aile interne 19 se déforme élastiquement entre un état au repos dans lequel aucune force extérieure n'est appliquée sur le cliquant et un état en charge dans lequel des forces extérieures opposées sont appliquées sur les ailes interne et externe 19, 20 du clinquant 18 de manière à les rapprocher l'une par rapport à l'autre.The inner wing 19 elastically deforms between a resting state in which no external force is applied to the clicker and a loaded state in which opposing external forces are applied to the inner and outer wings 19, 20 of the foil 18 so as to bring them closer to each other.

Le clinquant 18 passe d'un état au repos à un état en charge, lors de l'introduction du clinquant 18 dans le logement amont 12. A l'issue du montage du clinquant 18 dans le logement amont 12, l'aile interne 19 exerce une force de précontrainte (ou précharge) sur le becquet amont 17 au niveau du second point d'appui 23, cette force de précontrainte étant orientée radialement de l'intérieur vers l'extérieur. La force de précontrainte est directement liée à la force de rappel exercée par l'aile interne 19 sur la paroi interne 14 au niveau du premier appui 22, cette force de rappel étant orientée radialement de l'extérieur vers l'intérieur.The foil 18 passes from a state at rest to a loaded state, during the introduction of the foil 18 into the upstream housing 12. After mounting the foil 18 in the upstream housing 12, the internal flange 19 exerts a prestressing force (or preload) on the upstream spoiler 17 at the second fulcrum 23, this prestressing force being oriented radially from the inside to the outside. The preload force is directly related to the restoring force exerted by the inner flange 19 on the internal wall 14 at the level of the first support 22, this restoring force being oriented radially from the outside to the inside.

Avantageusement, un cliquant est réalisé dans un matériau résistant à la chaleur, par exemple un alliage à base cobalt et/ou nickel.Advantageously, a click is made of a heat resistant material, for example a cobalt and / or nickel based alloy.

Selon les modes de réalisation illustrés sur les figures, chaque secteur est mis en position sur le tambour 9 en introduisant respectivement les becquets amont et aval 17, 25 dans les logements amont et aval 12, 32 du tambour 9, le ou les clinquants 18 étant rapportés préalablement sur le becquet amont 17 du secteur correspondant.According to the embodiments illustrated in the figures, each sector is placed in position on the drum 9 by respectively introducing the upstream and downstream spoilers 17, 25 into the upstream and downstream housings 12, 32 of the drum 9, the foil (s) 18 being previously reported on the upstream spoiler 17 of the corresponding sector.

Ainsi, en position montée, l'aile externe 20 se trouve radialement entre la face externe 28 et la paroi externe 13. L'aile externe 20 est plaquée contre la paroi externe 13 sous l'action du becquet amont 17 qui est lui-même soumis à la force de précontrainte générée par la déformation élastique de l'aile interne 19 et/ou à la force centrifuge.Thus, in the mounted position, the outer wing 20 is located radially between the outer face 28 and the outer wall 13. The outer flange 20 is pressed against the outer wall 13 under the action of the upstream spoiler 17 which is itself subjected to the prestressing force generated by the elastic deformation of the inner flange 19 and / or to the centrifugal force.

L'âme 21 se trouve axialement entre la paroi amont 33 et la face amont 30, l'âme 21 pouvant être à fleur de la face amont 30 ou en appui sur la face amont 30.The core 21 is located axially between the upstream wall 33 and the upstream face 30, the core 21 possibly being flush with the upstream face 30 or resting on the upstream face 30.

L'aile interne 19 se trouve radialement entre la face interne 29 et la paroi interne 14. L'aile interne 19 exerce une force de précontrainte sur le becquet amont 17 au niveau du second appui 23 de manière à plaquer le becquet amont 17 contre la paroi externe 13 via l'aile externe 20.The internal wing 19 is located radially between the internal face 29 and the internal wall 14. The internal wing 19 exerts a prestressing force on the upstream spoiler 17 at the level of the second support 23 so as to press the upstream spoiler 17 against the outer wall 13 via the outer flange 20.

La force de précontrainte est prédéterminée de manière à plaquer le becquet amont 17 contre la paroi externe 13 dans les régimes de fonctionnement où la force centrifuge n'est pas suffisante pour le faire (à savoir lorsque les efforts aérodynamiques s'exerçant sur l'aubage sont supérieures à la force centrifuge), notamment lorsque la vitesse de rotation du rotor externe 4 est inférieur à un seuil prédéterminé. Les clinquants 18 permettent ainsi d'immobiliser les secteurs, et autrement dit d'éviter des mouvements résiduels (tels que le pivotement des secteurs), notamment lorsque la vitesse de rotation du rotor externe 4 est inférieur au seuil prédéterminé.The preload force is predetermined so as to press the upstream spoiler 17 against the outer wall 13 in operating speeds where the centrifugal force is not sufficient to do so (namely when the aerodynamic forces exerted on the blade are greater than centrifugal force), in particular when the speed of rotation of the outer rotor 4 is below a predetermined threshold. The foils 18 thus make it possible to immobilize the sectors, and in other words to avoid residual movements (such as the pivoting of the sectors), in particular when the speed of rotation of the outer rotor 4 is below the predetermined threshold.

En outre, la force de précontrainte est prédéterminée de manière à amortir les secteurs aubagés et ainsi réduire l'amplitude des efforts et des vibrations transmis au tambour 9. Le ou les clinquants 18 forment ainsi un amortisseur pour le secteur correspondant.In addition, the prestressing force is predetermined so as to damp the bladed sectors and thus reduce the amplitude of the forces and vibrations transmitted to the drum 9. The foil (s) 18 thus form a damper for the corresponding sector.

Pour ajuster la force de précontrainte, il est notamment possible de modifier les caractéristiques dimensionnelles ou géométriques de l'aile interne 19 et/ou le matériau de l'aile interne 19.To adjust the preload force, it is in particular possible to modify the dimensional or geometric characteristics of the inner flange 19 and / or the material of the inner flange 19.

En position montée, le becquet aval 25 est montée dans le logement aval 32 avec un jeu radial. Ainsi, en fonction du régime de fonctionnement, la face interne 29 est à fleur de la paroi interne 14 ou en appui sur la paroi interne 14 et la face externe 28 est à fleur de la paroi externe 13 ou en appui sur la paroi externe 13.In the mounted position, the downstream spoiler 25 is mounted in the downstream housing 32 with radial play. Thus, depending on the operating regime, the internal face 29 is flush with the internal wall 14 or rests on the internal wall 14 and the external face 28 is flush with the external wall 13 or rests on the external wall 13 .

En position montée, tel qu'illustré sur la figure 2, chaque secteur est maintenu axialement en position par au moins un anneau d'arrêt 36 logé en partie dans une rainure annulaire 37 pratiquée dans le tambour 9. L'anneau d'arrêt 36 est en partie logé dans la rainure 37 et en partie en appui axial contre une surface aval de la collerette 26 associée au becquet aval 25. Selon le mode de réalisation illustré sur les figures 2 à 4, chaque secteur aubagé comprend un unique cliquant, autrement dit le clinquant 18 s'étend circonférentiellement sur la longueur totale du becquet amont 17.In the mounted position, as shown on the figure 2 , each sector is held axially in position by at least one stop ring 36 housed in part in an annular groove 37 formed in the drum 9. The stop ring 36 is partly housed in the groove 37 and partly in axial bearing against a downstream surface of the flange 26 associated with the downstream spoiler 25. According to the embodiment illustrated in the figures 2 to 4 , each bladed sector comprises a single click, in other words the foil 18 extends circumferentially over the total length of the upstream spoiler 17.

Selon la variante de réalisation illustré sur la figure 6, chaque secteur aubagé comprend plusieurs clinquants 18 répartis circonférentiellement de manière régulière. Autrement dit, chaque clinquant 18 s'étend seulement sur une portion circonférentielle du becquet amont 17. Avantageusement, chaque secteur peut alors comprendre entre deux et dix clinquants 18.According to the variant embodiment illustrated on figure 6 , each bladed sector comprises several foils 18 distributed circumferentially in a regular manner. In other words, each foil 18 extends only over a circumferential portion of the upstream spoiler 17. Advantageously, each sector can then comprise between two and ten foils 18.

Selon le mode de réalisation illustré sur les figures 2 à 4, le clinquant 18 est clippé sur le becquet amont 17. Autrement dit, lors du montage du clinquant 18 sur le becquet amont 17, l'aile interne 19 est déformée élastiquement de sorte que l'aile interne 19 exerce une force de maintien sur le becquet amont 17 au niveau du second point d'appui 23, cette force de maintien étant orientée radialement de l'intérieur vers l'extérieur. Cette force de maintien permet de maintenir le clinquant 18 sur le secteur lors du montage du secteur sur le tambour 9.According to the embodiment illustrated on figures 2 to 4 , the foil 18 is clipped onto the upstream spoiler 17. In other words, when mounting the foil 18 on the upstream spoiler 17, the inner flange 19 is elastically deformed so that the inner flange 19 exerts a holding force on the upstream spoiler 17 at the second fulcrum 23, this holding force being oriented radially from the inside to the outside. This force of maintenance keeps the foil 18 on the sector when mounting the sector on the drum 9.

Selon une variante de réalisation illustré sur la figure 7, le becquet amont 17 comprend une protubérance 38 en saillie depuis sa face interne 29. La protubérance 38 est axialement disposée entre l'âme 21 et le second appui 23. Lors du montage du clinquant 18 sur le becquet amont 17, l'aile interne 19 est déformée élastiquement de manière à augmenter la distance entre l'aile interne 19 et l'aile externe 20, et ainsi permettre le passage de la protubérance 38. A l'issue du montage du clinquant 18, le clinquant 18 se retrouve ainsi bloqué axialement par la protubérance 38.According to an alternative embodiment illustrated in figure 7 , the upstream spoiler 17 comprises a protuberance 38 projecting from its internal face 29. The protuberance 38 is disposed axially between the core 21 and the second support 23. When mounting the foil 18 on the upstream spoiler 17, the internal wing 19 is elastically deformed so as to increase the distance between the inner flange 19 and the outer flange 20, and thus allow the passage of the protuberance 38. After mounting the foil 18, the foil 18 is thus blocked. axially by the protuberance 38.

Avantageusement, la protubérance 38 présente en section un profil arrondi, afin de faciliter le montage du clinquant 18 sur le becquet amont 17.Advantageously, the protuberance 38 has a rounded profile in section, in order to facilitate the mounting of the foil 18 on the upstream spoiler 17.

Claims (10)

Rotor (4) pour une turbine contrarotative (1) de turbomachine (2) comprenant un tambour (9) apte à être mis en rotation autour d'un axe longitudinal (X) et un aubage (10) monté radialement à l'intérieur du tambour (9), le tambour (9) comprenant un premier crochet interne (11) délimitant un premier logement (12) ouvert, le logement (12) présentant une paroi externe (13) et une paroi interne (14), l'aubage (10) comprenant au moins une pale (15) et une plateforme externe (16) pourvue d'un premier becquet (17) placé à l'intérieur dudit premier logement (12), caractérisé en ce que le rotor (4) comprend au moins un clinquant (18) rapporté sur le premier becquet (17), ledit clinquant (18) comprenant une aile interne (19) élastique et une aile externe (20) reliées l'une à l'autre via une âme (21), ladite aile externe (20) étant disposée radialement entre le premier becquet (17) et ladite paroi externe (13), ladite aile interne (19) présentant un premier appui (22) avec ladite paroi interne (14) et un second appui (23) avec le premier becquet (17), ladite aile interne (19) étant disposée dans le premier logement (12) de sorte à exercer une contrainte sur le premier becquet (17) au niveau dudit second appui (23) de manière à plaquer ledit premier becquet (17) contre ladite paroi externe (13) via ladite aile externe (20).Rotor (4) for a contra-rotating turbine (1) of a turbomachine (2) comprising a drum (9) capable of being rotated about a longitudinal axis (X) and a vane (10) mounted radially inside the drum (9), the drum (9) comprising a first internal hook (11) delimiting an open first housing (12), the housing (12) having an external wall (13) and an internal wall (14), the blade (10) comprising at least one blade (15) and an external platform (16) provided with a first spoiler (17) placed inside said first housing (12), characterized in that the rotor (4) comprises at at least one foil (18) attached to the first spoiler (17), said foil (18) comprising an elastic internal wing (19) and an external wing (20) connected to each other via a web (21), said outer wing (20) being disposed radially between the first spoiler (17) and said outer wall (13), said inner wing (19) having a first bearing (22) with said inner wall (14) ) and a second support (23) with the first spoiler (17), said inner wing (19) being disposed in the first housing (12) so as to exert a stress on the first spoiler (17) at the level of said second support ( 23) so as to press said first spoiler (17) against said outer wall (13) via said outer wing (20). Rotor (4) selon la revendication 1, caractérisé en ce que ladite plateforme externe (16) de l'aubage (10) comprend un second becquet (25) distant dudit premier becquet (17) et disposé axialement en aval dudit premier becquet (17), ledit second becquet (25) étant placé à l'intérieur d'un second logement (32) délimité par un second crochet interne (31) du tambour (9).Rotor (4) according to claim 1, characterized in that said outer platform (16) of the blade (10) comprises a second spoiler (25) remote from said first spoiler (17) and disposed axially downstream of said first spoiler (17) ), said second spoiler (25) being placed inside a second housing (32) delimited by a second internal hook (31) of the drum (9). Rotor (4) selon la revendication 2, caractérisé en ce que les premier et second becquets (17, 25) sont orientés chacun axialement de l'aval vers l'amont, lesdits premier et second logements (12, 32) étant ouverts axialement vers l'aval.Rotor (4) according to Claim 2, characterized in that the first and second spoilers (17, 25) are each oriented axially downstream towards upstream, said first and second housings (12, 32) being open axially downstream. Rotor (4) selon l'une des revendications précédentes, caractérisé en ce que le clinquant (18) est clippé sur ledit premier becquet (17).Rotor (4) according to one of the preceding claims, characterized in that the foil (18) is clipped onto said first spoiler (17). Rotor (4) selon l'une des revendications précédentes, caractérisé en ce que le premier becquet (17) comprend une protubérance (38) en saillie depuis une face interne (29), ladite protubérance (38) étant axialement disposée entre ladite âme (21) et ledit second appui (23).Rotor (4) according to one of the preceding claims, characterized in that the first spoiler (17) comprises a protrusion (38) projecting from an internal face (29), said protuberance (38) being axially disposed between said web ( 21) and said second support (23). Rotor (4) selon l'une des revendications précédentes, caractérisé en ce que le clinquant (18) est un anneau ou un secteur d'anneau.Rotor (4) according to one of the preceding claims, characterized in that the foil (18) is a ring or a ring sector. Rotor (4) selon l'une des revendications précédentes, caractérisé en ce que ladite aile interne (19) comprend un premier tronçon courbe (34) connecté directement à ladite âme (21) et un second tronçon courbe (35) connecté audit premier tronçon (34) via un point d'inflexion (I), lesdits premier et second appuis (22, 23) étant disposés respectivement au niveau dudit premier tronçon (34) et dudit second tronçon (35).Rotor (4) according to one of the preceding claims, characterized in that said internal wing (19) comprises a first curved section (34) connected directly to said web (21) and a second curved section (35) connected to said first section (34) via an inflection point (I), said first and second supports (22, 23) being respectively arranged at said first section (34) and said second section (35). Rotor (4) selon la revendication précédente, caractérisé en ce que ledit premier tronçon (34) est concave et ledit second tronçon (35) est convexe.Rotor (4) according to the preceding claim, characterized in that said first section (34) is concave and said second section (35) is convex. Turbine contrarotative (1) de turbomachine (2) comprenant un rotor (4) selon l'une des revendications précédentes.Counter-rotating turbine (1) of a turbomachine (2) comprising a rotor (4) according to one of the preceding claims. Turbomachine (2) comprenant une turbine contrarotative (1) selon la revendication précédente.Turbomachine (2) comprising a counter-rotating turbine (1) according to the preceding claim.
EP20161551.5A 2019-03-08 2020-03-06 Rotor for a counter-rotating turbine of a turbo machine Active EP3705684B1 (en)

Applications Claiming Priority (1)

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FR1902389A FR3093536B1 (en) 2019-03-08 2019-03-08 ROTOR FOR A CONTRAROTARY TURBINE OF TURBOMACHINE

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US11274557B2 (en) * 2019-11-27 2022-03-15 General Electric Company Damper assemblies for rotating drum rotors of gas turbine engines

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CN111663962B (en) 2024-10-18
FR3093536B1 (en) 2021-02-19
US20200284150A1 (en) 2020-09-10
US11454117B2 (en) 2022-09-27
EP3705684B1 (en) 2021-08-18
CN111663962A (en) 2020-09-15
FR3093536A1 (en) 2020-09-11

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