EP1764480B1 - Clinquant pour aube de turboréacteur - Google Patents

Clinquant pour aube de turboréacteur Download PDF

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Publication number
EP1764480B1
EP1764480B1 EP06120645A EP06120645A EP1764480B1 EP 1764480 B1 EP1764480 B1 EP 1764480B1 EP 06120645 A EP06120645 A EP 06120645A EP 06120645 A EP06120645 A EP 06120645A EP 1764480 B1 EP1764480 B1 EP 1764480B1
Authority
EP
European Patent Office
Prior art keywords
shim
tabs
foil
branches
connection part
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
EP06120645A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1764480A1 (fr
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/fr
Application granted granted Critical
Publication of EP1764480B1 publication Critical patent/EP1764480B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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

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.
  • a foil according to the prior art is known in the document FR 1 281 033 .
  • 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.
  • a fan disk 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 capable of wrapping the blade root 16. As shown in FIG. figure 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 on the figure 3 .
  • the tabs 22 are fixed by welding, riveting, bolting, or any other suitable fastening means, at the ends of the connecting piece 24.
  • a welding point 26 is formed between each lug 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 the figure 4 .
  • 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 middle part, so that the piece 24 is curved downstream, that is to say towards the blade root 16.
  • the curved portion of the part 24 flattens so that the part 24 stretches and allows the separation of the 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 can 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 on the 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 slideway 224 receiving said tabs 22 inside its two ends.
  • This slide 224 can be made, for example, by folding on itself a plate.
  • one of the tabs 22 is fixed at 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 following 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 lugs 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 tabs 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 Clinquant pour aube de turboréacteur Active EP1764480B1 (fr)

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 EP1764480A1 (fr) 2007-03-21
EP1764480B1 true EP1764480B1 (fr) 2008-11-05

Family

ID=36577386

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06120645A Active EP1764480B1 (fr) 2005-09-15 2006-09-14 Clinquant pour aube de turboréacteur

Country Status (9)

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

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FR2918703B1 (fr) * 2007-07-13 2009-10-16 Snecma Sa Ensemble de rotor de turbomachine
FR2918702B1 (fr) 2007-07-13 2009-10-16 Snecma Sa Clinquant pour aube de turbomachine
FR2921409B1 (fr) * 2007-09-25 2009-12-18 Snecma Clinquant pour aube de turbomachine.
US8206118B2 (en) * 2008-01-04 2012-06-26 United Technologies Corporation Airfoil attachment
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
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FR2951494B1 (fr) * 2009-10-15 2011-12-09 Snecma Clinquant pour aube de turbomachine.
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
FR2959527B1 (fr) * 2010-04-28 2012-07-20 Snecma Piece anti-usure pour echasse d'aube de soufflante de turboreacteur
FR2963383B1 (fr) * 2010-07-27 2016-09-09 Snecma Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
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FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
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
US10415402B2 (en) * 2013-03-13 2019-09-17 United Technologies Corporation Blade wear pads and manufacture methods
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FR3014477B1 (fr) 2013-12-06 2016-01-08 Turbomeca Rotor a aubes
FR3027071B1 (fr) 2014-10-13 2019-08-23 Safran Aircraft Engines Procede d'intervention sur un rotor et clinquant associe
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
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
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
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
FR3124824B1 (fr) 2021-07-01 2023-12-15 Safran Aircraft Engines Clinquant a languette nervurée
FR3124823B1 (fr) 2021-07-02 2023-11-17 Safran Aircraft Engines Encoche de verouillage de clinquant d’aube
FR3127522A1 (fr) 2021-09-24 2023-03-31 Safran Aircraft Engines Procede de preparation d’un pied d’une aube de turbomachine
FR3127986A1 (fr) 2021-10-11 2023-04-14 Safran Aircraft Engines Aube de turbine avec un pied comprenant un bloquage du clinquant
FR3129976A1 (fr) 2021-12-03 2023-06-09 Safran Aircraft Engines Ensemble comprenant un clinquant monte sur un disque d’une roue mobile
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Also Published As

Publication number Publication date
CA2558759C (fr) 2013-03-05
RU2006133128A (ru) 2008-03-20
US20100226777A1 (en) 2010-09-09
JP5068049B2 (ja) 2012-11-07
CA2558759A1 (fr) 2007-03-15
JP2007077993A (ja) 2007-03-29
EP1764480A1 (fr) 2007-03-21
DE602006003493D1 (de) 2008-12-18
US7938626B2 (en) 2011-05-10
RU2413072C2 (ru) 2011-02-27
FR2890684B1 (fr) 2007-12-07
ES2317437T3 (es) 2009-04-16
CN1932251B (zh) 2010-09-29
FR2890684A1 (fr) 2007-03-16
CN1932251A (zh) 2007-03-21

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