[go: up one dir, main page]

EP3705684B1 - Rotor für eine gegenläufige turbine einer turbomaschine - Google Patents

Rotor für eine gegenläufige turbine einer turbomaschine Download PDF

Info

Publication number
EP3705684B1
EP3705684B1 EP20161551.5A EP20161551A EP3705684B1 EP 3705684 B1 EP3705684 B1 EP 3705684B1 EP 20161551 A EP20161551 A EP 20161551A EP 3705684 B1 EP3705684 B1 EP 3705684B1
Authority
EP
European Patent Office
Prior art keywords
spoiler
rotor
foil
upstream
section
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.)
Active
Application number
EP20161551.5A
Other languages
English (en)
French (fr)
Other versions
EP3705684A1 (de
Inventor
Patrick Jean Laurent Sultana
Olivier Renon
Laurent Cédric ZAMAI
Clément Charles Jérémy COIFFIER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3705684A1 publication Critical patent/EP3705684A1/de
Application granted granted Critical
Publication of EP3705684B1 publication Critical patent/EP3705684B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • 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
    • 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 disc.
  • 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 whose head 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 blade 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 internal wing being arranged 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 rotational speed of the rotor is lower. at a predetermined threshold.
  • the foil makes it possible to damp the blading and thus 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 each other, 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.
  • An exhaust gas flow 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 core 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 external wall 13 via the external 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 regularly.
  • 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 collar 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 an upstream hook) and a second downstream internal hook 31 (hereinafter referred to as a 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
  • 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 can 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 flange 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 supports 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 approximately halfway up 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 state under load, 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 prestressing 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 wing 19 and / or to 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 the 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 less than 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 or shims 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 retaining 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 web 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.
  • the protuberance 38 has a rounded profile in section, in order to facilitate the mounting of the foil 18 on the upstream spoiler 17.

Landscapes

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

Claims (10)

  1. Rotor (4) für gegenläufige Turbine (1) einer Turbomaschine (2), der eine Trommel (9) umfasst, die geeignet ist, um eine Längsachse (X) in Drehung versetzt zu werden, und eine Beschaufelung (10), die radial in dem Inneren der Trommel (9) montiert ist, wobei die Trommel (9) einen ersten Innenhaken (11) umfasst, der eine erste offene Aufnahme (12) abgrenzt, wobei die Aufnahme (12) eine Außenwand (13) und eine Innenwand (14) aufweist, die Beschaufelung (10) mindestens eine Schaufel (15) umfasst, und eine Außenplattform (16), die mit einem ersten Spoiler (17), der in dem Inneren der ersten Aufnahme (12) platziert ist, versehen ist,
    dadurch gekennzeichnet, dass der Rotor (4) mindestens eine Folie (18) umfasst, die an den ersten Spoiler (17) angebaut ist, wobei die Folie (18) einen elastischen Innenflügel (19) und einen Außenflügel (20) umfasst, die miteinander über eine Seele (21) verbunden sind, wobei der Außenflügel (20) radial zwischen dem ersten Spoiler (17) und der Außenwand (13) angeordnet ist, der Innenflügel (19) eine erste Auflage (22) mit der Innenwand (14) und eine zweite Auflage (23) mit dem ersten Spoiler (17) aufweist, wobei der Innenflügel (19) in der ersten Aufnahme (12) derart angeordnet ist, dass er eine Belastung auf den ersten Spoiler (17) im Bereich der zweiten Auflage (23) derart ausübt, dass der erste Spoiler (17) gegen die Außenwand (13) über den Außenflügel (20) angedrückt ist.
  2. Rotor (4) nach Anspruch ein, dadurch gekennzeichnet, dass die Außenplattform (16) der Beschaufelung (10) einen zweiten Spoiler (25), der von dem ersten Spoiler (17) beabstandet ist umfasst und der axial stromabwärts des ersten Spoiler (17) angeordnet ist, wobei der zweite Spoiler (25) in dem Inneren einer zweiten Aufnahme (32), die von einem zweiten Innenhaken (31) der Trommel (9) abgegrenzt ist, platziert ist.
  3. Rotor (4) nach Anspruch 2, dadurch gekennzeichnet, dass der erste und der zweite Spoiler (17, 25) jeweils axial von stromabwärts nach stromaufwärts ausgerichtet sind, wobei die erste und die zweite Aufnahme (12, 32) axial nach stromabwärts offen sind.
  4. Rotor (4) nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Folie (18) auf den ersten Spoiler (17) geclipst ist.
  5. Rotor (4) nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der erste Spoiler (17) einen Vorsprung (38) umfasst, der von einer Innenfläche (29) vorragt, wobei der Vorsprung (38) axial zwischen der Seele (21) und der zweiten Auflage (23) angeordnet ist.
  6. Rotor (4) nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Folie (18) eine Ring oder ein Ringsektor ist.
  7. Rotor (4) nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Innenflügel (19) einen ersten gekrümmten Abschnitt (34) umfasst, der direkt mit der Seele (21) verbunden ist, und einen zweiten gekrümmten Abschnitt (35), der mit dem ersten Abschnitt (34) über einen Biegepunkt (I) verbunden ist, wobei die erste und die zweite Auflage (22, 23) jeweils im Bereich des ersten Abschnitts (34) des zweiten Abschnitts (35) angeordnet sind.
  8. Rotor (4) nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass der erste Abschnitt (34) konkav und der zweite Abschnitt (35) konvex ist.
  9. Gegenläufige Turbine (1) einer Turbomaschine (2), die einen Rotor (4) nach einem der vorstehenden Ansprüche umfasst.
  10. Turbomaschine (2), das eine gegenläufige Turbine (1) nach dem vorstehenden Anspruch umfasst.
EP20161551.5A 2019-03-08 2020-03-06 Rotor für eine gegenläufige turbine einer turbomaschine Active EP3705684B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1902389A FR3093536B1 (fr) 2019-03-08 2019-03-08 Rotor pour une turbine contrarotative de turbomachine

Publications (2)

Publication Number Publication Date
EP3705684A1 EP3705684A1 (de) 2020-09-09
EP3705684B1 true EP3705684B1 (de) 2021-08-18

Family

ID=67185392

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20161551.5A Active EP3705684B1 (de) 2019-03-08 2020-03-06 Rotor für eine gegenläufige turbine einer turbomaschine

Country Status (4)

Country Link
US (1) US11454117B2 (de)
EP (1) EP3705684B1 (de)
CN (1) CN111663962B (de)
FR (1) FR3093536B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11274557B2 (en) * 2019-11-27 2022-03-15 General Electric Company Damper assemblies for rotating drum rotors of gas turbine engines

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4171930A (en) * 1977-12-28 1979-10-23 General Electric Company U-clip for boltless blade retainer
US4159624A (en) * 1978-02-06 1979-07-03 Gruner George P Contra-rotating rotors with differential gearing
FR2641573B1 (fr) * 1989-01-11 1991-03-15 Snecma Rotor de turbomachine muni d'un dispositif de fixation des aubes
US5131814A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure
US5131813A (en) 1990-04-03 1992-07-21 General Electric Company Turbine blade outer end attachment structure
US5307622A (en) 1993-08-02 1994-05-03 General Electric Company Counterrotating turbine support assembly
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
US7048496B2 (en) * 2002-10-31 2006-05-23 General Electric Company Turbine cooling, purge, and sealing system
FR2866073B1 (fr) * 2004-02-11 2006-07-28 Snecma Moteurs Turboreacteur ayant deux soufflantes contrarotatives solidaires d'un compresseur a basse pression contrarotatif
US7172388B2 (en) * 2004-08-24 2007-02-06 Pratt & Whitney Canada Corp. Multi-point seal
WO2009082281A1 (en) * 2007-12-20 2009-07-02 Volvo Aero Corporation Gas turbine engine
FR2942273B1 (fr) 2009-02-18 2011-06-10 Snecma Moteur double flux a roues de turbine contrarotatives
JP5646517B2 (ja) * 2009-03-09 2014-12-24 スネクマ タービンリング組立体
FR2975428B1 (fr) * 2011-05-17 2015-11-20 Snecma Roue a aubes de turbomachine
US8727735B2 (en) * 2011-06-30 2014-05-20 General Electric Company Rotor assembly and reversible turbine blade retainer therefor
FR2978793B1 (fr) * 2011-08-03 2015-12-04 Snecma Rotor de turbine pour une turbomachine
FR2986836B1 (fr) * 2012-02-09 2016-01-01 Snecma Tole annulaire anti-usure pour une turbomachine
US9103213B2 (en) * 2012-02-29 2015-08-11 General Electric Company Scalloped surface turbine stage with purge trough
FR3003301B1 (fr) * 2013-03-14 2018-01-05 Safran Helicopter Engines Anneau de turbine pour turbomachine
US20170167438A1 (en) * 2015-12-11 2017-06-15 General Electric Company Gas Turbine Engine

Also Published As

Publication number Publication date
FR3093536A1 (fr) 2020-09-11
CN111663962A (zh) 2020-09-15
EP3705684A1 (de) 2020-09-09
US20200284150A1 (en) 2020-09-10
FR3093536B1 (fr) 2021-02-19
US11454117B2 (en) 2022-09-27
CN111663962B (zh) 2024-10-18

Similar Documents

Publication Publication Date Title
EP1584794B1 (de) Turbomaschinenrotorscheibe mit einer Axialhalterung für die Laufschaufeln
EP1970537B1 (de) Gebläse eines Turbotriebwerks
EP1793093B1 (de) Leitschaufeln einer verbesserten Turbomaschine
EP1873385B1 (de) Abgasendstück zur Führung eines Gasstroms stromab einer Turbine
FR2943312A1 (fr) Helice non carenee a pales a calage variable pour une turbomachine
EP2406462B1 (de) Rotorelement mit einem fluidkanal und einem kanalsperrglied sowie turbomotor mit dem rotorelement
FR2943313A1 (fr) Helice non carenee a pales a calage variable pour une turbomachine
EP1598524B1 (de) Verfahren der Montage beschaufelter Rotorscheiben und Dämpfungsvorrichung dieser Schaufeln
EP2060751B1 (de) Turbinen- oder Kompressorstufe eines Turbotriebwerks
FR3108370A1 (fr) Etage d’aubes a calage variable pour une turbomachine
FR3085712A1 (fr) Aube de roue mobile pour turbomachine d'aeronef, presentant un talon decouple de la pale de l'aube
FR2971022A1 (fr) Etage redresseur de compresseur pour une turbomachine
FR2978793A1 (fr) Rotor de turbine pour une turbomachine
EP3705684B1 (de) Rotor für eine gegenläufige turbine einer turbomaschine
EP3710679B1 (de) Vorrichtung zum halten eines radialen zentripetalen elements zur luftprobenentnahme
EP3430238A1 (de) Turbinenrotor mit einem belüftungsabstandshalter
FR3057904A1 (fr) Dispositif d'amortissement ameliore pour compresseur de turbomachine
FR3029564A1 (fr) Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
FR3079553A1 (fr) Ensemble pour turbomachine
WO2023247903A1 (fr) Ensemble aubagé pour turbomachine, turbine pour turbomachine et turbomachine
FR3008455A1 (fr) Redresseur pour compresseur comportant des moyens de rattrapage de jeu
FR3106615A1 (fr) Ensemble pour turbomachine
FR3137721A1 (fr) Ensemble de turbine de turbomachine
FR3139859A1 (fr) Ensemble d’un dispositif d'aubes à calage variable
FR2915511A1 (fr) Limitation de survitesse du rotor d'une turbine de turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20200306

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 1/26 20060101ALI20210319BHEP

Ipc: F01D 5/30 20060101ALI20210319BHEP

Ipc: F01D 5/10 20060101ALI20210319BHEP

Ipc: F01D 5/03 20060101AFI20210319BHEP

INTG Intention to grant announced

Effective date: 20210416

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602020000393

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

Ref country code: AT

Ref legal event code: REF

Ref document number: 1421818

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210915

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210818

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1421818

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210818

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211118

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211220

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211118

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211119

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602020000393

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20220519

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20220331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220306

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220306

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220331

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230331

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240220

Year of fee payment: 5

Ref country code: GB

Payment date: 20240220

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20200306

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20240220

Year of fee payment: 5

Ref country code: IT

Payment date: 20240220

Year of fee payment: 5

Ref country code: FR

Payment date: 20240221

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210818