EP1764480A1 - Zwischenstück für eine Schaufel eines Turbinentriebwerks - Google Patents

Zwischenstück für eine Schaufel eines Turbinentriebwerks Download PDF

Info

Publication number
EP1764480A1
EP1764480A1 EP06120645A EP06120645A EP1764480A1 EP 1764480 A1 EP1764480 A1 EP 1764480A1 EP 06120645 A EP06120645 A EP 06120645A EP 06120645 A EP06120645 A EP 06120645A EP 1764480 A1 EP1764480 A1 EP 1764480A1
Authority
EP
European Patent Office
Prior art keywords
foil
connecting piece
tabs
blade
branches
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
EP06120645A
Other languages
English (en)
French (fr)
Other versions
EP1764480B1 (de
Inventor
Jean-Bernard Forgue
Jack-Pierre Lauvergnat
Thierry Nitre
Patrick Reghezza
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1764480A1 publication Critical patent/EP1764480A1/de
Application granted granted Critical
Publication of EP1764480B1 publication Critical patent/EP1764480B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing

Definitions

  • the invention relates to a foil for turbomachine blade comprising two branches adapted to come wrap the sides of the foot of the blade.
  • the invention may relate to a foil for a turbojet fan blade.
  • the foil and the root of the blade are intended to be positioned inside a housing formed by an axial groove formed in the fan disk.
  • This housing is open upstream but delimited downstream by a wall.
  • This wall is formed by the upstream face of the drum of the low pressure compressor of the turbojet engine. It should be noted that this drum is generally of relatively low thickness at this point.
  • an axial direction is defined as being a direction parallel to the axis of rotation of the fan.
  • upstream and downstream of a part are defined with respect to the normal direction of flow of the gases inside the turbojet engine.
  • the invention aims to avoid this last problem by proposing a foil for turbomachine blade comprising two branches adapted to come wrap the flanks of the foot of the blade, and two legs extending respectively from one end of the two branches, these two tabs being folded towards each other, characterized in that said tabs are interconnected so as not to unfold.
  • said tabs are long enough to be folded over one another and be directly connected to each other.
  • they can be connected by welding, riveting, bolting or by interlocking into one another.
  • the foil comprises a connecting piece connecting said tabs so as to prevent them from unfolding.
  • This second embodiment makes it possible to produce shorter tabs and, generally, of less complex shape than those of the first embodiment.
  • the connecting piece used may have different shapes. Furthermore, the connecting piece can be fixed to the legs, that is to say be assembled with the legs so as to prevent relative movement between it and the legs or, conversely, be assembled with the legs with some relative freedom of movement.
  • the blade root can move inside the foil in directions other than the axial direction.
  • the connecting piece is assembled to the legs so as to allow the spacing of the branches of the foil (which amounts to allow the spacing of said legs) and therefore the "lateral" movements of the foot of dawn inside the foil.
  • the connecting piece may be a slide receiving said tabs inside its two ends.
  • the two tabs are assembled at the ends of the slideway so as to remain both free in translation in the direction of spacing of the branches of the foil, or one of these tabs is fixed to the slide, for example by welding, while the other remains free in translation.
  • FIGS. 1 to 3 show: a fan disc 2 having at its periphery numerous axial grooves 4 defining with the upstream face 8 of the low-pressure compressor drum 6 a housing 10 capable of receiving a shim 12, a foil 20 and the foot 16 of a blade 14. It will be noted that there are similar assemblies without wedge 12.
  • the foil 20 comprises two lateral branches 21A and 21B and is suitable for wrapping the blade root 16. As shown in FIG. 2, the foil 20 rests on the shim 12.
  • the blade root 16, the shim 12, the drum 6 and the fan disk 2 are made, for example, of titanium alloy.
  • the foil 20, meanwhile, is a wear part made of a harder alloy such as the alloy known under the brand Inconel 718, and has the function of limiting the wear of the blade root 16 and the disc of 2. Since the foil 20 is made of a material harder than that of the drum 6, repeated shocks between these two elements would damage the drum.
  • the foil 20 has two lugs 22 which extend from its upstream end, on each side of the blade root and which are folded towards each other. These tabs 22 are connected by a connecting piece 24 which prevents them from unfolding.
  • the upstream and downstream of the foil and the other parts are defined with respect to the normal flow direction of the gases inside the turbojet, represented by the arrow F in FIG.
  • the lugs 22 are fixed by welding, riveting, bolting, or any other suitable fastening means, at the ends of the connecting piece 24.
  • a welding spot 26 is made between each leg 22 and the part 24.
  • the connecting piece 24 is able to stretch in the direction of separation of the branches 21A and 21B, that is to say in a direction parallel to the transverse axis A shown in FIG.
  • the connecting piece 24 may be a flexible blade of which at least a portion is curved or bent.
  • the connecting piece 24 is a flexible blade having several folds 28 in its median part, so that the piece 24 is convex downstream, that is to say towards the When the branches 21A, 21B and their respective tabs 22 seek to deviate along the axis A, the curved portion of the piece 24 flattens out so that the piece 24 stretches and allows the blade to be extended. spacing branches 21A and 21B.
  • the piece 24 is curved towards the blade root 16 housed inside the foil 20, that is to say here downstream, helps cushion the shocks between the foil 20 and the foot dawn 16 because the curved portion 25 deforms (it flattens) when it abuts against the blade root 16.
  • the curved portion maintains the welds 26 and the tabs 22 away from the foot of the d dawn 16 and thus preserves these parts of the shocks.
  • the connecting piece 124 may be curved upstream.
  • the curved portion 125 does not come into contact with the blade root 16 (it has no damping function) but it still allows the piece 124 to stretch.
  • the curved portion 25, 125 may have folds and / or at least one curved portion.
  • the curved portion 125 is formed by a curved portion while in Figure 5 the curved portion 25 has five planar sides separated by four folds. Note that the more the curved portion 25 has folds, the more easily it deforms, which promotes the stretching of the piece 24 and the damping of the foil 22 on the blade root 16.
  • said connecting piece is a slide 224 receiving said tabs 22 within its two ends.
  • This slide 224 can be made, for example, by folding on itself a plate.
  • one of the tabs 22 is attached to one end of the part of the link 224 while the other leg 22 is assembled at the other end of the connecting piece 224 so as to remain free in translation in the direction of separation of the branches, that is to say parallel to the transverse axis A '.
  • Fixing at least one of the tabs 22 to the connecting piece 24 allows to have a single set to handle. In addition, it avoids any risk of detachment of the connecting part in operation.
  • the two legs 22 of the foil 20 overlap and are fixed to one another. They can be fastened together, for example, by a weld point 26.
  • a weld point 26 To allow the foil to stretch in the direction A "spacing branches 21A, 21B, at least one of said legs is a flexible blade of which a portion At least one is bent or folded
  • the two lugs 22 have a domed portion 325 facing downstream and formed by a curved portion, alternatively, this convex portion 325 could have folds.
  • the two lugs 22 of the foil 20 overlap and are nested so as to remain free in translation in the direction of separation of the branches.
  • one of the tabs 22 has two upper and lower wings 23 folded so as to form a slide inside which the other leg 22 can slide.
  • one of the tabs 22 has an oblong opening inside which slides a nipple. Either this stud is fixed on the other tab 22, or it also slides inside an oblong opening formed on this other tab 22.
  • turbojet fan blade foil examples have been described above. These foils could nonetheless be used for other types of turbomachine blades such as, for example, a turbojet low pressure compressor blade.
  • the part of the turbojet engine to be protected that is to say the drum of the low pressure compressor 6, is located downstream of the foil. Consequently, the tabs 22 extend from the upstream end of the foil 20.
  • the tabs 22 extend from the downstream end of the foil 20.

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)
EP06120645A 2005-09-15 2006-09-14 Zwischenstück für eine Schaufel eines Turbinentriebwerks Active EP1764480B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0509420A FR2890684B1 (fr) 2005-09-15 2005-09-15 Clinquant pour aube de turboreacteur

Publications (2)

Publication Number Publication Date
EP1764480A1 true EP1764480A1 (de) 2007-03-21
EP1764480B1 EP1764480B1 (de) 2008-11-05

Family

ID=36577386

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06120645A Active EP1764480B1 (de) 2005-09-15 2006-09-14 Zwischenstück für eine Schaufel eines Turbinentriebwerks

Country Status (9)

Country Link
US (1) US7938626B2 (de)
EP (1) EP1764480B1 (de)
JP (1) JP5068049B2 (de)
CN (1) CN1932251B (de)
CA (1) CA2558759C (de)
DE (1) DE602006003493D1 (de)
ES (1) ES2317437T3 (de)
FR (1) FR2890684B1 (de)
RU (1) RU2413072C2 (de)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2014873A1 (de) * 2007-07-13 2009-01-14 Snecma Metallfolie für Laufradschaufel eines Turbotriebwerks
FR2921409A1 (fr) * 2007-09-25 2009-03-27 Snecma Sa Clinquant pour aube de turbomachine.
FR2951494A1 (fr) * 2009-10-15 2011-04-22 Snecma Clinquant pour aube de turbomachine.
FR2959527A1 (fr) * 2010-04-28 2011-11-04 Snecma Piece anti-usure pour echasse d'aube de soufflante de turboreacteur
EP2077376A3 (de) * 2008-01-04 2012-04-25 United Technologies Corporation Befestigung einer Verbundwerkstoffrotorschaufel in einer Gasturbine
WO2015082808A1 (fr) * 2013-12-06 2015-06-11 Turbomeca Rotor a aubes
EP2766576B1 (de) * 2011-10-10 2018-08-01 Safran Aircraft Engines Kühlung des schwalbenschwanzes zur befestigung einer turbomaschinenschaufel
FR3120911A1 (fr) 2021-03-16 2022-09-23 Safran Aircraft Engines Aube comprenant un membre d’attache résistant au frottement et roue mobile comprenant une telle aube d’une turbine axiale de turbomachine
FR3124218A1 (fr) 2021-06-21 2022-12-23 Safran Aircraft Engines Clinquant a languette longue pour pied d’aube de rotor de turbomachine
WO2023275456A1 (fr) 2021-07-02 2023-01-05 Safran Aircraft Engines Clinquant, aube de rotor, ensemble pour rotor de turbomachine et rotor
FR3124824A1 (fr) 2021-07-01 2023-01-06 Safran Aircraft Engines Clinquant a languette nervurée
FR3127986A1 (fr) 2021-10-11 2023-04-14 Safran Aircraft Engines Aube de turbine avec un pied comprenant un bloquage du clinquant
WO2023099856A1 (fr) 2021-12-03 2023-06-08 Safran Aircraft Engines Ensemble comprenant un clinquant monte sur un disque d'une roue mobile de turbomachine et roue mobile
EP4553286A1 (de) * 2023-11-10 2025-05-14 RTX Corporation Verschleisspad für den fuss einer gebläseschaufel

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918703B1 (fr) * 2007-07-13 2009-10-16 Snecma Sa Ensemble de rotor de turbomachine
FR2934873B1 (fr) * 2008-08-06 2011-07-08 Snecma Dispositif amortisseur de vibrations pour attaches d'aubes.
US8047778B2 (en) * 2009-01-06 2011-11-01 General Electric Company Method and apparatus for insuring proper installation of stators in a compressor case
FR2945074B1 (fr) * 2009-04-29 2011-06-03 Snecma Cale d'aube de soufflante renforcee
DE102009024845A1 (de) * 2009-06-09 2010-12-16 Howaldtswerke-Deutsche Werft Gmbh Propeller
JP5444932B2 (ja) * 2009-08-19 2014-03-19 株式会社Ｉｈｉ 動翼の固定装置、翼回転装置及び翼回転装置の組立方法
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
FR2963383B1 (fr) * 2010-07-27 2016-09-09 Snecma Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
GB2477825B (en) * 2010-09-23 2015-04-01 Rolls Royce Plc Anti fret liner assembly
US8225614B2 (en) * 2010-10-07 2012-07-24 General Electric Company Shim for sealing transition pieces
US9246372B2 (en) * 2012-01-20 2016-01-26 Fluor Technologies Corporation Rotor pole support ribs in gearless drives
US10273816B2 (en) 2013-02-12 2019-04-30 United Technologies Corporation Wear pad to prevent cracking of fan blade
WO2014143318A1 (en) * 2013-03-13 2014-09-18 United Technologies Corporation Blade wear pads and manufacture methods
EP3058179B1 (de) * 2013-10-11 2020-01-15 United Technologies Corporation Komprimierbare gebläseschaufel mit blattwurzelzwischenstück
US9464531B2 (en) * 2013-10-16 2016-10-11 General Electric Company Locking spacer assembly
FR3027071B1 (fr) 2014-10-13 2019-08-23 Safran Aircraft Engines Procede d'intervention sur un rotor et clinquant associe
CN104500447A (zh) * 2014-12-14 2015-04-08 惠阳航空螺旋桨有限责任公司 风洞轴流压缩机风扇
CN104500446A (zh) * 2014-12-14 2015-04-08 惠阳航空螺旋桨有限责任公司 风洞轴流压缩机转子复合材料叶片根部连接结构
US10378371B2 (en) 2014-12-18 2019-08-13 United Technologies Corporation Anti-rotation vane
US10087948B2 (en) * 2015-03-30 2018-10-02 United Technologies Corporation Fan blade and method of covering a fan blade root portion
EP3075961A1 (de) * 2015-04-02 2016-10-05 Siemens Aktiengesellschaft Leitschaufelanordnung
US9772313B2 (en) * 2015-04-21 2017-09-26 The Boeing Company Method and apparatus for identifying shim geometries
US10738626B2 (en) 2017-10-24 2020-08-11 General Electric Company Connection assemblies between turbine rotor blades and rotor wheels
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
FR3127522B1 (fr) 2021-09-24 2025-09-05 Safran Aircraft Engines Procede de preparation d’un pied d’une aube de turbomachine
CN114042695B (zh) * 2022-01-13 2022-04-29 中国民航大学 一种飞机发动机风扇叶片清洗润滑设备
FR3136507B1 (fr) * 2022-06-13 2025-10-10 Safran Aircraft Engines Dispositif de retenue axiale des aubes mobiles d’une turbine BP dans les alvéoles d’un disque de rotor de la turbine BP et procédé de montage de ces aubes mobiles
US12410720B2 (en) * 2023-11-02 2025-09-09 General Electric Company Turbine engine having a rotatable disk and a blade
FR3159628A1 (fr) 2024-02-26 2025-08-29 Safran Aircraft Engines Clinquant pour disque de turbomachine, disque de turbomachine correspondant.

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2971743A (en) * 1957-08-14 1961-02-14 Gen Motors Corp Interlocked blade shrouding
FR1281033A (fr) * 1961-02-15 1962-01-08 Daimler Benz Ag Montage d'aubes mobiles en céramique sur des machines à rotors centrifuges traversés axialement par des courants, en particulier sur des turbines à gaz
GB1355554A (en) * 1970-09-25 1974-06-05 Gen Electric Turbomachinery bladed rotors
US4102602A (en) * 1976-08-31 1978-07-25 Volkswagenwerk Aktiengesellschaft Rotor for an axial turbine
US4980241A (en) * 1988-05-10 1990-12-25 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Foil insert in a joint between machine components

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2667327A (en) * 1950-06-14 1954-01-26 Westinghouse Electric Corp Rotor construction
GB914548A (en) 1960-03-04 1963-01-02 Daimler Benz Ag Improvements relating to wheel discs with ceramic blades for axial-flow machines
JPS4942888Y1 (de) * 1968-06-25 1974-11-25
SU881354A2 (ru) 1980-01-04 1981-11-15 Предприятие П/Я В-2285 Устройство дл уплотнени рабочих лопаток турбины
GB8922339D0 (en) * 1989-10-04 1989-11-22 Rolls Royce Plc Improvements in or relating to labyrinth seal structures
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5423831A (en) * 1991-01-24 1995-06-13 Nates; Colin Clamp
SE469717B (sv) * 1992-02-20 1993-08-30 Ingemar Naeslund Klaemma, speciellt foer tillslutning av paasar
JPH07247804A (ja) * 1993-01-07 1995-09-26 General Electric Co <Ge> ガスタービンエンジン用のロータ及び動翼アセンブリ、並びに多層被覆シム
JPH10317907A (ja) * 1997-05-22 1998-12-02 Hitachi Ltd 圧縮機翼固定構造
US6212742B1 (en) * 1999-01-29 2001-04-10 Abb Power T & D Company Inc. Drip tray clamps for transformer fuse holders
CN2378627Y (zh) * 1999-02-04 2000-05-17 珠海市南产业电器有限公司 一种用于圣诞灯串的线夹
US6431835B1 (en) * 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
US6513767B1 (en) * 2001-09-04 2003-02-04 J. Linn Rodgers Ergonomic encirclement
JP2003314369A (ja) * 2002-04-26 2003-11-06 Ishikawajima Harima Heavy Ind Co Ltd ダブテールシム
US6860722B2 (en) * 2003-01-31 2005-03-01 General Electric Company Snap on blade shim

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2971743A (en) * 1957-08-14 1961-02-14 Gen Motors Corp Interlocked blade shrouding
FR1281033A (fr) * 1961-02-15 1962-01-08 Daimler Benz Ag Montage d'aubes mobiles en céramique sur des machines à rotors centrifuges traversés axialement par des courants, en particulier sur des turbines à gaz
GB1355554A (en) * 1970-09-25 1974-06-05 Gen Electric Turbomachinery bladed rotors
US4102602A (en) * 1976-08-31 1978-07-25 Volkswagenwerk Aktiengesellschaft Rotor for an axial turbine
US4980241A (en) * 1988-05-10 1990-12-25 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Foil insert in a joint between machine components

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918702A1 (fr) * 2007-07-13 2009-01-16 Snecma Sa Clinquant pour aube de turbomachine
EP2014873A1 (de) * 2007-07-13 2009-01-14 Snecma Metallfolie für Laufradschaufel eines Turbotriebwerks
FR2921409A1 (fr) * 2007-09-25 2009-03-27 Snecma Sa Clinquant pour aube de turbomachine.
EP2042689A1 (de) * 2007-09-25 2009-04-01 Snecma Dämpfungsblech für die Schaufel einer Turbomaschine
RU2469193C2 (ru) * 2007-09-25 2012-12-10 Снекма Прокладка для лопатки газотурбинного двигателя
US8535011B2 (en) 2007-09-25 2013-09-17 Snecma Shim for a turbomachine blade
EP2077376A3 (de) * 2008-01-04 2012-04-25 United Technologies Corporation Befestigung einer Verbundwerkstoffrotorschaufel in einer Gasturbine
FR2951494A1 (fr) * 2009-10-15 2011-04-22 Snecma Clinquant pour aube de turbomachine.
US9500091B2 (en) 2010-04-28 2016-11-22 Snecma Wear-resistant part for the support of a blade of a turbojet fan
FR2959527A1 (fr) * 2010-04-28 2011-11-04 Snecma Piece anti-usure pour echasse d'aube de soufflante de turboreacteur
WO2012072903A1 (fr) * 2010-04-28 2012-06-07 Snecma Piece anti-usure pour echasse d'aube de soufflante de turboreacteur
EP2766576B1 (de) * 2011-10-10 2018-08-01 Safran Aircraft Engines Kühlung des schwalbenschwanzes zur befestigung einer turbomaschinenschaufel
CN105814281B (zh) * 2013-12-06 2018-05-25 涡轮梅坎公司 装有叶片的转子
CN105814281A (zh) * 2013-12-06 2016-07-27 涡轮梅坎公司 装有叶片的转子
FR3014477A1 (fr) * 2013-12-06 2015-06-12 Turbomeca Rotor a aubes
RU2660985C1 (ru) * 2013-12-06 2018-07-11 Турбомека Ротор с лопатками
WO2015082808A1 (fr) * 2013-12-06 2015-06-11 Turbomeca Rotor a aubes
US10858946B2 (en) 2013-12-06 2020-12-08 Safran Helicopter Engines Bladed rotor
FR3120911A1 (fr) 2021-03-16 2022-09-23 Safran Aircraft Engines Aube comprenant un membre d’attache résistant au frottement et roue mobile comprenant une telle aube d’une turbine axiale de turbomachine
FR3124218A1 (fr) 2021-06-21 2022-12-23 Safran Aircraft Engines Clinquant a languette longue pour pied d’aube de rotor de turbomachine
FR3124824A1 (fr) 2021-07-01 2023-01-06 Safran Aircraft Engines Clinquant a languette nervurée
FR3124823A1 (fr) 2021-07-02 2023-01-06 Safran Aircraft Engines Encoche de verouillage de clinquant d’aube
WO2023275456A1 (fr) 2021-07-02 2023-01-05 Safran Aircraft Engines Clinquant, aube de rotor, ensemble pour rotor de turbomachine et rotor
US20240337192A1 (en) * 2021-07-02 2024-10-10 Safran Aircraft Engines Foil, rotor blade, assembly for a turbomachine rotor and rotor
US12372000B2 (en) 2021-07-02 2025-07-29 Safran Aircraft Engines Foil, rotor blade, assembly for a turbomachine rotor and rotor
FR3127986A1 (fr) 2021-10-11 2023-04-14 Safran Aircraft Engines Aube de turbine avec un pied comprenant un bloquage du clinquant
WO2023099856A1 (fr) 2021-12-03 2023-06-08 Safran Aircraft Engines Ensemble comprenant un clinquant monte sur un disque d'une roue mobile de turbomachine et roue mobile
FR3129976A1 (fr) 2021-12-03 2023-06-09 Safran Aircraft Engines Ensemble comprenant un clinquant monte sur un disque d’une roue mobile
EP4553286A1 (de) * 2023-11-10 2025-05-14 RTX Corporation Verschleisspad für den fuss einer gebläseschaufel
US12352184B2 (en) 2023-11-10 2025-07-08 Rtx Corporation Wear pad for root of fan blade

Also Published As

Publication number Publication date
RU2413072C2 (ru) 2011-02-27
ES2317437T3 (es) 2009-04-16
FR2890684A1 (fr) 2007-03-16
CA2558759A1 (fr) 2007-03-15
CN1932251B (zh) 2010-09-29
JP2007077993A (ja) 2007-03-29
DE602006003493D1 (de) 2008-12-18
CA2558759C (fr) 2013-03-05
CN1932251A (zh) 2007-03-21
EP1764480B1 (de) 2008-11-05
US7938626B2 (en) 2011-05-10
JP5068049B2 (ja) 2012-11-07
FR2890684B1 (fr) 2007-12-07
US20100226777A1 (en) 2010-09-09
RU2006133128A (ru) 2008-03-20

Similar Documents

Publication Publication Date Title
EP1764480B1 (de) Zwischenstück für eine Schaufel eines Turbinentriebwerks
CA2640003C (fr) Clinquant pour aube de turbomachine
CA2644335C (fr) Etage de turbine ou de compresseur, en particulier de turbomachine
CA2634942C (fr) Perfectionnement a une cale intercalee entre un pied d&#39;aube et le fond de l&#39;alveole du disque dans laquelle il est monte
EP2286094B1 (de) Klemme zum zusammenhalten zweier teile
EP2448814B1 (de) Rumpfelement mit einem rumpfsegment und übergangsvorrichtung
EP2007991B1 (de) Klemmvorrichtung
FR2939835A1 (fr) Joint d&#39;etancheite de plateforme dans un rotor de turbomachine, methode pour ameliorer l&#39;etancheite entre une plateforme et une aube de turbomachine.
EP1503044B1 (de) Zwischenschaufelplattformen mit elastischen Seitenkanten
EP1850017A2 (de) Selbstsperrende Verbindung zwischen einem Flachteil und einer Stange mit kugelförmigem Ende
EP3055594B1 (de) Dichtung für einen schubumkehrer einer turbodüsen-triebwerksgondel
EP3020996A1 (de) Schwimmsattelbremse, die eine zentrale elastische rückholfeder eines externen bremsbelags umfasst, die ausgleichsmittel des verschleissspiels umfasst, feder und ersatzteilkit
EP1535840B1 (de) Anordnung mit einer Befestigungsvorrichtung für eine Verkleidung zwischen einem Lufteinlass eines Flugzeugtriebwerkes und eines Pylons
EP1213483A1 (de) Statorstufe eines Verdichters
CA2587096C (fr) Ensemble pour compresseur de moteur d&#39;aeronef comprenant des aubes a attache marteau a pied incline
FR2529269A1 (fr) Systeme d&#39;assemblage elastique de deux pieces
CA2577502C (fr) Roue de rotor de turbomachine
FR3054009A1 (fr) Accessoire pour ensemble formant raccord avec systeme anti-perforation
CA2475152A1 (fr) Plate-forme inter-aubes a pions de fixation et contraintes de cisaillement variables, pour un disque de support d&#39;aubes de turboreacteur
FR2877059A1 (fr) Biellette de commande destinee a l&#39;entrainement d&#39;une aube a calage variable
FR2710103A1 (fr) Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
EP2525247B1 (de) Brillengestell mit Gelenk
FR2732083A1 (fr) Dispositif de connexion a montage simplifie pour assembler deux profiles
EP4375518B1 (de) Befestigungsvorrichtung
FR2853218A1 (fr) Ensemble de fenetre comprenant une tringle

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: 20060914

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE ES FR GB IT NL

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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): DE ES FR GB IT NL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602006003493

Country of ref document: DE

Date of ref document: 20081218

Kind code of ref document: P

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2317437

Country of ref document: ES

Kind code of ref document: T3

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: 20090806

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

Ref country code: ES

Payment date: 20120910

Year of fee payment: 7

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20141007

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: 20130915

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006003493

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE GBR, DE

Ref country code: DE

Ref legal event code: R082

Ref document number: 602006003493

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE EGBR, DE

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

Ref country code: DE

Payment date: 20250919

Year of fee payment: 20

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

Ref country code: NL

Payment date: 20250922

Year of fee payment: 20

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

Ref country code: GB

Payment date: 20250923

Year of fee payment: 20

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

Ref country code: FR

Payment date: 20250923

Year of fee payment: 20

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

Ref country code: IT

Payment date: 20250930

Year of fee payment: 20