EP2373872B1 - Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque - Google Patents

Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque Download PDF

Info

Publication number
EP2373872B1
EP2373872B1 EP09803826A EP09803826A EP2373872B1 EP 2373872 B1 EP2373872 B1 EP 2373872B1 EP 09803826 A EP09803826 A EP 09803826A EP 09803826 A EP09803826 A EP 09803826A EP 2373872 B1 EP2373872 B1 EP 2373872B1
Authority
EP
European Patent Office
Prior art keywords
disk
blade
axial
turbine wheel
retention device
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
EP09803826A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2373872A2 (fr
Inventor
Denis Chanteloup
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 Helicopter Engines SAS
Original Assignee
Turbomeca SA
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 Turbomeca SA filed Critical Turbomeca SA
Priority to PL09803826T priority Critical patent/PL2373872T3/pl
Publication of EP2373872A2 publication Critical patent/EP2373872A2/fr
Application granted granted Critical
Publication of EP2373872B1 publication Critical patent/EP2373872B1/fr
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
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys

Definitions

  • the invention relates generally to paddle wheels in gas turbines and more particularly to the axial retention of said blades relative to the axis of the wheel.
  • the field of application of the invention is in particular that of industrial gas turbines and aeronautical gas turbine engines.
  • a turbine wheel conventionally comprises a plurality of blades, a disk and an axial blade retainer.
  • Each blade generally has a blade profile, a platform and a fastener.
  • At the periphery of the disk are mounted the blades, the attachment of each of the blades being engaged in a housing opening at the periphery of the disk and extending axially between two opposite faces of the disk, the housing being separated by teeth.
  • the axial blade retainer axially locks the blades relative to the axis of rotation of the disk.
  • the invention aims to provide a turbine wheel in which the blades undergo substantially less vibration during operation of the wheel.
  • platform of said blade has a projection projecting axially beyond one of the faces of the disc, said projection comprising a second stop member, and the axial projection, the second stop member and said face of the disc form a groove oriented towards the axis of the disc, said groove being intended to receive the axial retaining device, so that the axial retaining device, in mounted position, abuts in the first axial direction against the second stop member and against said face of the disk in a second axial direction opposite to the first axial direction, whereby said blade is locked relative to the disk in the second axial direction.
  • the axial retaining device axially locks the blade relative to the disk. Indeed, the blade is blocked axially on the one hand by the first stop member of the disk and on the other hand by the axial retaining device.
  • the first stop member blocks the blade axially in the first axial direction
  • the axial retainer blocks the blade axially in the second axial direction.
  • axial is meant a direction oriented along the axis of the wheel or disk.
  • the blade is retained in the housing by shape cooperation between the blade and two teeth of the disk, in a manner known per se.
  • the first axial direction is that in which the blades are inserted into the disk housing while the second axial direction is that by which the blades can be removed from the disk.
  • the platform of the blade has an axial projection comprising a second stop member.
  • the axial projection is provided to extend axially beyond one of the faces of the disk when the blade is mounted on the disk.
  • the second stop member is located under the platform and protrudes radially towards the axis of the disc.
  • said disk face, the axial projection and the second stop member form a groove oriented towards the axis of the disk.
  • the lower face of the platform, opposite to the face bearing the blade profile forms the bottom of the groove while said face of the disc and the second stop member form the side edges of the groove.
  • the groove thus defined is intended to receive the axial retention device.
  • the axial retention device is held in the groove in the first axial direction by the second stop member and in the second axial direction by said face of the disk.
  • the axial retention device is also maintained in the radial direction in the centrifugal direction by the bottom of the groove.
  • this plating makes it possible to maintain the axial retention device at the bottom of the groove. Indeed, the plating ensures that the axial retention device remains properly housed in the groove between the side edges. Therefore, the axial retainer can hardly disengage from the groove.
  • this plating advantageously allows a mechanical coupling between the blade and the axial retention device.
  • the relative flexibility of the axial retention device with respect to the rigidity of the blade and the rigidity of the disk allows a damping of the azimuthal component of the vibrations.
  • the axial retention of the blades on the disk is properly ensured and on the other hand the vibrations of the blade are damped.
  • At least one boss is provided between the axial retaining device and said blade to make a mechanical contact between the blade and the axial retaining device.
  • a boss between the blade and the axial retention device improves the mechanical contact between the blade and the axial retaining device, said mechanical contact for damping vibration of the blade.
  • this boss may possibly make it possible to brake the possible movements of the axial retention device in an azimuthal direction, which improves the safety of the axial retention of the blades.
  • the boss is formed on the axial retainer.
  • the boss is formed under the axial projection, at the bottom of said groove, that is to say on the face which is opposite the axial retaining device.
  • a recess of complementary shape to the boss is formed on the element facing the boss, and formed so that the boss comes to lodge in the recess.
  • the boss is formed on the axial retention device, the element facing the boss is the platform and the recess is made under the platform. Conversely, if the boss is formed under the platform, the element facing the boss is the axial retention device and the recess is formed at the axial retaining device.
  • a recess of complementary shape to the boss makes it possible to further improve the mechanical contact between the blade and the axial retention device by combining the advantages associated with the presence of a simple boss and the advantages related to the presence of facing surfaces without boss. .
  • the boss allows permanent contact, and the facing surfaces being very close thanks to the recess of complementary shape to the boss allow additional contact during the rotation of the wheel due to the centrifugal force.
  • the fact that the boss is housed in a recess also prevents the rotation of the axial retention device.
  • the boss and / or the recess are made on a portion of the platform that does not radially support the blade profile.
  • the boss With this arrangement of the boss relative to the blade profile, it is understood that the boss is not located near a radially supporting zone blade profile, the boss is arranged under the platform or on the retainer axial. Thus the mechanical stresses resulting from the interactions between the blade and the axial retention device are applied in an area where the platform is weakly mechanically stressed. Indeed, the areas of the platform close to the blade profile are typically substantially solicited by the blade profile.
  • the disk has an anti-rotation cleat capable of blocking the azimuthal movements of the axial retaining device with respect to the disk.
  • An anti-rotation cleat makes it possible to ensure that the axial retention device does not itself rotate when the rotation of the wheel.
  • the axial retention device remains correctly positioned.
  • this anti-rotation cleat is made in such a way that it guarantees the balance of the wheel.
  • the anti-rotation tab balances the mass of the axial retainer which is not necessarily evenly distributed over the entire wheel.
  • the assembly composed by the axial retaining device and the anti-rotation cleat has a uniformly distributed mass on the wheel and does not imbalance when the latter rotates.
  • the disc also has at least one safety catch able to block the centripetal movements of the axial retention device.
  • a safety catch thus arranged makes it possible to block the axial retention device radially in the groove.
  • the safety of the axial locking is thus further improved.
  • the wheel according to the invention comprises three safety catches uniformly distributed radially every 120 ° angle on the disk.
  • the axial retention device is a split annular ring.
  • This annular ring has the advantage of being a single member for retaining all the blades on the disc.
  • the fact that the ring is split gives it some flexibility vis-à-vis the radial deformations, which is advantageous from the point of view of damping azimuthal vibrations of the blades.
  • the ring is advantageously elastic, which allows on the one hand damping of the vibrations of the blades, and on the other hand to facilitate the mounting operation of the latter on the wheel.
  • annular ring as axial retention device allows for a simultaneous mechanical coupling of the rod with several blades.
  • the ring also achieves a satisfactory damping of the vibrations of each blade which makes it possible to avoid their ruin.
  • the ring is prestressed so as to be in contact with a contact pressure with the platform, which ensures the position of the ring relative to the wheel at the stop of the machine.
  • the second stop member forms a spoiler, and preferably, the spoiler forms a ring portion extending over at least a portion of the azimuthal length of the axial projection of the blade platform.
  • This preferred form of the second stop member makes it possible to distribute the axial retention forces at the platform of the blade and thus to avoid local peaks of mechanical stresses.
  • the present invention also relates to a turbomachine comprising a turbine wheel according to the invention.
  • the figure 1 represents an exemplary embodiment of a turbine wheel 10 according to the invention.
  • the wheel 10 is composed of a disc 12 having an axis A, a plurality of blades 14 and an axial retaining device 16.
  • the axial retaining device 16 is a split annular rod.
  • ring or “split ring” for "axial retention device”.
  • Each of the blades 14 has a fastener 140 in the form of a fir tree, a platform 142 and a blade profile 144.
  • the fastener 140 is engaged in a housing 120 of the disk 12.
  • the housing 120 extend axially between two opposite faces of the disc, and are separated by teeth 121.
  • Each blade 14 is retained radially at its attachment 140 by the two adjacent teeth 121 at the clip.
  • the disk 12 is equipped with three safety catches 122 arranged at 120 ° angle to each other on the disk. These safety catches 122 hold the rod 16 in its radial position with respect to the disk 12 and the blades 14.
  • the disk 12 is also equipped with an anti-rotation cleat 124 to lock the rod 16 in its azimuthal position with respect to the disk 12 and the blades 14.
  • the anti-rotation tab 124 is inserted into the slot of the ring 16.
  • the Figure 2A represents an angular portion of the wheel 10 of the figure 1 exploded. On this Figure 2A the first stop members 126 and the second stop members 146 are visible. When the blades are mounted on the disc 12 in a first axial direction X, the first stop members 126 are housed in cavities 148 of the blades 14.
  • the second stop members 146 are arranged on the lower face of the platform 142 on an axial projection of the platform 150 projecting from the face 128 of the disc 12.
  • Each second stop member 146 forms a spoiler so that when mounting a blade 14 on the disc 12 from the face 130 of the disc 12, the blade attachment 140 can slide in the housing 120 until the first stop member 126 is housed in a cavity 148
  • each spoiler has an additional machining on its azimuth flanges so as not to interfere with the teeth 121 during assembly. Subsequently, the term "spoiler" will be used for "second stop device".
  • each spoiler 146 forms a ring portion, so that when the blades 14 are mounted on the disc 12, the set of spurs 146 form a discontinuous ring.
  • the Figure 2B represents the wheel portion described in the Figure 2A in an assembled manner.
  • the underside of the axial projection 150, the face 128 of the disc, and the face of the spoiler 146 facing the face 128 of the disc 12 (or facing the blade attachment 140) form a groove oriented towards the axis.
  • the rod 16 is housed in this groove.
  • the figure 3 is a sectional view of the example shown on the Figure 2B according to the sectional plan III.
  • the blade 14 of the figure 3 is engaged in its housing 120 in the first axial direction X until one of the contact faces 152 of the platform 142 comes into abutment against the first stop member 126 of the disk 12.
  • the blade is blocked according to the first axial direction X.
  • the ring 16 is disposed under the projection 150, between the face 154 of the blade attachment 140 which is in the extension of the face 128 of the disk 12, and the face 156 of the spoiler 146 which is opposite the face 154.
  • the blade is retained axially in the second axial direction Y opposite the first axial direction X, by the spoiler 146 which abuts against the rod 16 which itself bears against the face 128 of the disc 12 and the first stop member 126 (cf. fig.3 ).
  • the blade is retained in the two opposite axial directions X and Y through the interaction of the axial retention device 16, on the one hand with the first stop member 126 and on the other hand with the second stop member 146.
  • the platform 142 is provided with at least one boss 170.
  • This boss 170 is on the underside of the platform 142, and more particularly on the underside of the axial projection 150 More specifically, considering the groove in which the rod 16 is housed, the boss 170 is formed on the bottom of this groove.
  • the boss 170 is not disposed directly above the blade profile 144, that is to say that in the axial direction, the blade profile 144 and the boss 170 are staggered. .
  • the blade profile 144 is supported radially by the portion of the platform supported by the attachment of the blade 140 and does not impinge on the axial projection 150.
  • the boss 170 is not located on a part of the platform 142 which radially supports the blade profile 144.
  • FIGS. 5A to 5E represent different variants of ring / platform interfaces according to the section plane V of the figure 4 .
  • the Figure 5A corresponds to the embodiment represented by the figure 4 .
  • a single boss 170 is represented by the Figure 5A .
  • the ring / platform interface is realized by a contact between the boss 170 and the rod 16.
  • the surface 160 of the rod 16 facing the bottom of the groove 158 is substantially smooth.
  • the Figure 5B represents an alternative embodiment in which, unlike the embodiment previously described, the rod 16 has a plurality of bosses 162 positioned along the circumference of the rod (a single boss is shown) while the bottom of the groove 158 is smooth.
  • FIGS 5C and 5D respectively similar to Figures 5A and 5B , represent bosses 170 and 162 arranged in a recess of complementary shape arranged opposite said boss.
  • the bosses 170 are under the platforms 142 while the rod 16 has recesses of complementary shape.
  • the bosses 162 are formed on the circumference of the rod 16 while the recesses are formed in the blade platforms 142.
  • the rod 16 is then advantageously maintained in the azimuthal direction by the interaction between the bosses and the bosses. recesses of complementary shape.
  • the figure 5E is a variant combining the simultaneous presence of bosses and recesses on the rod 16 and the projection 150.
  • the figure 6 represents a turbomachine 200 equipped with a turbine wheel according to the invention.
  • the gas generator turbine wheel 210 and the free turbine wheel 220 are in accordance with the present invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09803826A 2008-12-11 2009-12-10 Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque Active EP2373872B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09803826T PL2373872T3 (pl) 2008-12-11 2009-12-10 Wirnik turbiny wyposażony w urządzenie do ustalania osiowego ryglujące łopatki względem tarczy

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0858461A FR2939832B1 (fr) 2008-12-11 2008-12-11 Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.
PCT/FR2009/052469 WO2010067024A2 (fr) 2008-12-11 2009-12-10 Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque

Publications (2)

Publication Number Publication Date
EP2373872A2 EP2373872A2 (fr) 2011-10-12
EP2373872B1 true EP2373872B1 (fr) 2012-12-05

Family

ID=41056780

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09803826A Active EP2373872B1 (fr) 2008-12-11 2009-12-10 Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque

Country Status (11)

Country Link
US (1) US8956119B2 (ru)
EP (1) EP2373872B1 (ru)
JP (1) JP5726747B2 (ru)
KR (1) KR101672065B1 (ru)
CN (1) CN102245859B (ru)
CA (1) CA2746431C (ru)
ES (1) ES2399851T3 (ru)
FR (1) FR2939832B1 (ru)
PL (1) PL2373872T3 (ru)
RU (1) RU2507400C2 (ru)
WO (1) WO2010067024A2 (ru)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
FR2988128A1 (fr) * 2012-03-19 2013-09-20 Alstom Technology Ltd Rotor de turbine pour une centrale thermoelectrique
US9476310B2 (en) * 2012-10-18 2016-10-25 General Electric Company Systems and methods to axially retain blades
EP2803821A1 (en) * 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Blade device, blade system, and corresponding method of manufacturing a blade system
US9664056B2 (en) 2013-08-23 2017-05-30 General Electric Company Turbine system and adapter
FR3026429B1 (fr) * 2014-09-30 2016-12-09 Snecma Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor
KR101628613B1 (ko) * 2015-04-01 2016-06-08 두산중공업 주식회사 버켓의 축방향 고정장치
KR101689085B1 (ko) 2015-08-03 2017-01-02 두산중공업 주식회사 터빈용 마지막 버켓 고정장치 및 이를 이용한 마지막 버켓의 조립 방법
DE102016107315A1 (de) 2016-04-20 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Rotor mit Überhang an Laufschaufeln für ein Sicherungselement
US11609114B2 (en) * 2016-06-27 2023-03-21 University Of Pretoria Method and system for monitoring rotor blades of a turbomachine using blade tip timing (BTT)
US10724384B2 (en) * 2016-09-01 2020-07-28 Raytheon Technologies Corporation Intermittent tab configuration for retaining ring retention
KR101953462B1 (ko) * 2017-05-24 2019-02-28 두산중공업 주식회사 베인 어셈블리를갖는 가스터빈
CN108757569A (zh) * 2018-06-07 2018-11-06 哈尔滨电气股份有限公司 新型压气机叶片和轮盘连接结构
FR3091719B1 (fr) * 2019-01-15 2021-02-12 Safran Aircraft Engines secteur de flasque d’etancheite de disque de rotor
JP7213835B2 (ja) * 2020-02-10 2023-01-27 三菱重工業株式会社 タービンホイール

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB699582A (en) * 1950-11-14 1953-11-11 Rolls Royce Improvements in or relating to gas-turbine engines
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
SU443192A1 (ru) * 1972-11-14 1974-09-15 Моторостроительное конструкторское бюро Устройство дл уплотнени рабочих лопаток турбины
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
FR2345605A1 (fr) * 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
SU903572A1 (ru) * 1980-05-16 1982-02-07 Предприятие П/Я В-2504 Рабочее колесо турбомашины
EP0236337B1 (en) * 1985-09-12 1989-03-01 Solar Turbines Incorporated Seal ring means for a bladed rotor assembly
FR2603333B1 (fr) * 1986-09-03 1990-07-20 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
FR2639063A1 (fr) * 1988-11-17 1990-05-18 Snecma Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine
US5256035A (en) * 1992-06-01 1993-10-26 United Technologies Corporation Rotor blade retention and sealing construction
FR2694046B1 (fr) * 1992-07-22 1994-09-23 Snecma Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes.
US5302086A (en) * 1992-08-18 1994-04-12 General Electric Company Apparatus for retaining rotor blades
DE19960896A1 (de) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine
CZ20002685A3 (cs) * 1999-12-20 2001-08-15 General Electric Company Zařízení pro uchycení lopatek otáčivého stroje a způsob jejich uchycení
FR2888897B1 (fr) * 2005-07-21 2007-10-19 Snecma Dispositif d'amortissement des vibrations d'un anneau de retention axiale des aubes de soufflante d'une turbomachine
CN101258305B (zh) * 2005-09-07 2011-06-15 西门子公司 用于对转子中的动叶片进行轴向固定的装置、用于一种这样的装置的密封件以及一种这样的装置的应用

Also Published As

Publication number Publication date
RU2507400C2 (ru) 2014-02-20
US20110311366A1 (en) 2011-12-22
ES2399851T3 (es) 2013-04-03
KR20110098935A (ko) 2011-09-02
FR2939832B1 (fr) 2011-01-07
CA2746431A1 (fr) 2010-06-17
JP5726747B2 (ja) 2015-06-03
WO2010067024A2 (fr) 2010-06-17
JP2012511663A (ja) 2012-05-24
FR2939832A1 (fr) 2010-06-18
US8956119B2 (en) 2015-02-17
PL2373872T3 (pl) 2013-05-31
WO2010067024A3 (fr) 2010-08-05
CN102245859A (zh) 2011-11-16
CN102245859B (zh) 2014-04-30
RU2011128021A (ru) 2013-01-20
CA2746431C (fr) 2016-06-07
EP2373872A2 (fr) 2011-10-12
KR101672065B1 (ko) 2016-11-02

Similar Documents

Publication Publication Date Title
EP2373872B1 (fr) Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque
EP2488725B1 (fr) Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
EP1873401B1 (fr) Rotor de turbomachine et turbomachine comportant un tel rotor
EP1598524B1 (fr) Procédé d'assemblage de disques aubagés monoblocs et dispositif d'amortissement des vibrations des aubes de ces disques
EP1180580B1 (fr) Dispositif de rétention d'une flasque annulaire contre une face radiale d'un disque à aubes
EP1584784B1 (fr) Dispositif d'assemblage de brides annulaires, en particulier dans une turbomachine
CA2746979C (fr) Roue de turbine avec systeme de retention axiale des aubes
EP0695856B1 (fr) Disque de compresseur de turbomachine muni d'une gorge circulaire asymétrique
FR2866069A1 (fr) Turboreacteur a soufflante solidaire d'un arbre d'entrainement supporte par un premier et un deuxieme paliers
WO2005082542A2 (fr) Bol de pulverisation, projecteur rotatif incorporant un tel bol et installation de projection incorporant un tel projecteur
FR2666623A1 (fr) Roue de turbomachine a pales rapportees.
CA2598532A1 (fr) Aube de rotor d'une turbomachine
FR2899636A1 (fr) Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine
FR3047124A1 (fr) Ensemble de support d'un moteur electrique, notamment dans un dispositif de chauffage, ventilation et/ou climatisation pour vehicule automobile
FR2492031A1 (fr) Poulie de variateur de vitesse
EP2053199B1 (fr) Roue de turbomachine
EP0691455A1 (fr) Joint métallique à levre et turbomachine équippé de ce joint
FR2949138A1 (fr) Turbomachine comportant des moyens d'anti-rotation d'un ecrou de palier
EP3705684B1 (fr) Rotor pour une turbine contrarotative de turbomachine
EP1331402B1 (fr) Dispositif de commande d'aube variable
FR3073907A1 (fr) Organe de retention pour plateforme de turbomachine
WO2020178490A1 (fr) Ensemble pour une turbine de turbomachine
FR3047122A1 (fr) Ensemble de support d'un moteur electrique, notamment dans un dispositif de chauffage, ventilation et/ou climatisation pour vehicule automobile
FR3106615A1 (fr) Ensemble pour turbomachine
EP4228964A1 (fr) Ensemble d'attache pour une aube 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

17P Request for examination filed

Effective date: 20110707

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): 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 SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/32 20060101ALI20120604BHEP

Ipc: F01D 5/30 20060101AFI20120604BHEP

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): 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 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: AT

Ref legal event code: REF

Ref document number: 587410

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121215

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602009011816

Country of ref document: DE

Effective date: 20130131

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2399851

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20130403

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 587410

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121205

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

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: 20121205

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: 20121205

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: 20130305

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: 20121205

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20121205

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

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: 20121205

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: 20121205

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: 20130306

REG Reference to a national code

Ref country code: PL

Ref legal event code: T3

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: 20121205

BERE Be: lapsed

Owner name: TURBOMECA

Effective date: 20121231

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 NON-PAYMENT OF DUE FEES

Effective date: 20121231

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: 20121205

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: 20121205

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: 20130305

Ref country code: IS

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: 20130405

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

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: 20130405

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: 20121205

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: 20121205

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20121231

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

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: 20121205

Ref country code: IE

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

Effective date: 20121210

26N No opposition filed

Effective date: 20130906

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: 20121205

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: 20121205

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602009011816

Country of ref document: DE

Effective date: 20130906

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

Ref country code: TR

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: 20121205

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: 20121210

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: 20121205

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

Effective date: 20091210

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: 20131231

Ref country code: CH

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

Effective date: 20131231

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: 20121205

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN HELICOPTER ENGINES, FR

Effective date: 20170727

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

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

Ref country code: ES

Payment date: 20190102

Year of fee payment: 10

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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

Ref country code: SE

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

Effective date: 20191211

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20210601

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

Ref country code: ES

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

Effective date: 20191211

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

Ref country code: GB

Payment date: 20231121

Year of fee payment: 15

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

Ref country code: FR

Payment date: 20231122

Year of fee payment: 15

Ref country code: DE

Payment date: 20231121

Year of fee payment: 15

Ref country code: CZ

Payment date: 20231124

Year of fee payment: 15

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

Ref country code: PL

Payment date: 20231127

Year of fee payment: 15

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

Ref country code: IT

Payment date: 20231121

Year of fee payment: 15