EP1384539A1 - Metallischer Verbundkörper und Verfahren seiner Herstellung - Google Patents

Metallischer Verbundkörper und Verfahren seiner Herstellung Download PDF

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Publication number
EP1384539A1
EP1384539A1 EP03291800A EP03291800A EP1384539A1 EP 1384539 A1 EP1384539 A1 EP 1384539A1 EP 03291800 A EP03291800 A EP 03291800A EP 03291800 A EP03291800 A EP 03291800A EP 1384539 A1 EP1384539 A1 EP 1384539A1
Authority
EP
European Patent Office
Prior art keywords
metal matrix
mechanical part
core
metal
reinforcing elements
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
EP03291800A
Other languages
English (en)
French (fr)
Other versions
EP1384539B1 (de
Inventor
Isabelle Peslerbe
Jacques Tschofen
Anne Thenaisie
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
Forges de Bologne
Original Assignee
Forges de Bologne
SNECMA Moteurs 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 Forges de Bologne, SNECMA Moteurs SA filed Critical Forges de Bologne
Publication of EP1384539A1 publication Critical patent/EP1384539A1/de
Application granted granted Critical
Publication of EP1384539B1 publication Critical patent/EP1384539B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C2204/00—End product comprising different layers, coatings or parts of cermet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49908—Joining by deforming
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49908—Joining by deforming
    • Y10T29/49909—Securing cup or tube between axially extending concentric annuli
    • Y10T29/49913—Securing cup or tube between axially extending concentric annuli by constricting outer annulus
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component

Definitions

  • the present invention relates to obtaining a coin having a main direction along which extend a heart zone forming a core and a peripheral zone forming an envelope surrounding said core, said core and said envelope having a metallurgical bond between them, said core being made of a first material having at least one matrix metal and said envelope being made of a second material having at least one metal matrix.
  • the present invention relates to obtaining a mechanical part for which the matrix of the first material and / or the second material aluminum as base metal.
  • the invention relates to a mechanical part used in the sector aeronautics, particularly as a moving or fixed blade of a compressor, especially low pressure, or as a dawn blower ("fan”) of turbojet.
  • the present invention is not intended to be limited to the realization of blades or to be applied only to the sector aeronautics: other types of mechanical parts may be envisaged, in particular in the machine tool sectors or in the automotive sector, such as crankcases, tubes, cylinders or wearing parts in the field of braking.
  • titanium alloys are widely used in This has the disadvantages of significant costs of raw material as well as a weight sometimes still considered too important.
  • the present invention aims to overcome the disadvantages of these techniques of the prior art by proposing a piece mechanics and its manufacturing process using techniques metallurgical simple to implement.
  • the present invention thus relates to a mechanical part with a main direction along which extend a heart zone forming a core and a zone peripheral forming an envelope surrounding said core, said core and said envelope having a metallurgical bond between them, said core being made of a first material having at least one metal matrix and said envelope being made in a second material having at least one metal matrix.
  • said metal matrices of first and second materials have the same base metal and at least one of said first and second materials is formed of a metal matrix composite comprising elements of reinforcement dispersed in said metal matrix.
  • the characteristics of the interface between two materials forming a room, which can therefore be described as complex, are of great importance, especially when at least one of these materials is a metal matrix composite: the identity between the re-entrant base metal in the composition of the first and second materials is in this regard of great importance in obtaining a core and an envelope forming between them a metallurgical bond presenting a great mechanical resistance.
  • this arrangement allows, by the presence of reinforcement elements, in at least one of the first material and the second material, to improve the strength properties mechanical and, possibly, withstand temperature, of the piece in the part that we wish to strengthen, while at the same time density similar to that of the metal matrix.
  • both the first material and the second material (core and shell) is (are) made up of a metal matrix composite comprising elements of reinforcement dispersed in said metal matrix.
  • the composition of the first material is different from that of the second material, at least as far as the proportion of reinforcement elements.
  • a blade consisting of said mechanical part.
  • Such a dawn can belong to a compressor, especially low pressure, whether as a fixed dawn or as dawn mobile.
  • the present invention relates to the manufacturing process which makes it possible, by means of its implementation, to obtain said aforesaid mechanical part.
  • said step a) consists in forming jointly the core and the envelope by the metallurgical technique of powders.
  • this technique which implements the compression of a powder in a matrix, followed by a heat treatment called "sintering", it is thus possible to obtain a metal part forming directly the semi-finished product.
  • This first solution is particularly well adapted to the situation in which one wishes to obtain a mechanical part where said reinforcement elements represent a percentage by weight of the composition of said progressive metal matrix composite in said first material (core) and in said second material (envelope), from the center of said core to the periphery of said envelope, or decreasing from the center, either increasing from the center, entering through example, a minimum of 0% to 10% and a maximum less than or equal to 50% by weight.
  • This second solution is particularly well adapted to situation in which one wishes to obtain a mechanical part where said reinforcing elements are only present in one of the first and second materials, the other of said first and second materials being formed only of said metal matrix.
  • Sub-step a4) of the second solution of step a), consists of preferably rolling or spinning all, that is to say by successive passages, in force and hot, between pairs of cylinders more and more close together or in sectors of section smaller and smaller.
  • this step a) uses a technique performing the compaction, in particular the pressurization between the core and envelope, at the time of their joint formation (first solution), either at the moment of their initial training as a separate parts (second solution), so as to create between materials constituting a metallurgical type connection generating a good interface.
  • forging generally consists of metallurgical operation whose purpose is to convert ingots into shaped blanks by deformation of a metal carried to a temperature where it is sufficiently malleable, the deformation being obtained either by shock (pestle, sheep) or by pressure (presses with closed matrix) between two tools.
  • this forging step consists of stamping or stamping.
  • Other forging possibilities can also be used alone, or in combination with the stamping: press forging, pestle ...
  • the manufacturing method according to the present invention applies to a first material which is formed only of said metal matrix which comprises aluminum as base metal and a second material which is formed of said matrix composite metal comprising said reinforcing elements dispersed in said metal matrix, said metal matrix having aluminum as base metal and said reinforcing elements being formed of silicon carbide particles (SiC): this preferential choice makes it possible to benefit from a very good interaction between an aluminum alloy and SiC particles, as explained in US 6,135,195, for a material whose price is lower than that of titanium.
  • SiC silicon carbide particles
  • step a) the choice of aluminum as base metal allows benefit from its good elongation properties, especially for the forging step and also, in the case of the second solution of step a), during step a4) of passage in a more sectional orifice reduced (rolling or spinning), as well as its good resistance to corrosion.
  • Figure 1 An example of the possible applications of the mechanical part according to the present invention is shown in Figure 1 in the form of a double-flow turbojet engine 100.
  • This turbojet engine 100 comprises a conventional structure which comprises different elements arranged axially around the axis longitudinal 102, in fluid communication with each other, namely in particular a blower 104 and an accelerator 106.
  • turbojet engine includes the others conventional elements of such a structure, namely a compressor high pressure, a combustion chamber, a high pressure turbine and a low pressure turbine, these different additional elements not represented for the sake of clarity.
  • the fan 104 and the accelerator 106 are rotated by the low pressure turbine thanks to the rotor axis 108.
  • the blower 104 comprises a series of blades 110 extending radially mounted on an annular disc 112: only one of these vanes appear in Figure 1. It is understood that the disc 112 and the blades 110 are rotatably mounted about the axis 102 of the motor 100.
  • the motor 100 further comprises a fan casing 114.
  • the accelerator 106 includes several sets of blades 116 in rotation mounted on a disc 118 and between which are mounted series of vanes 120.
  • the present invention relates to obtaining a coin mechanics that can constitute in particular each of the blades 110 of the blower 104 and / or each of the blades 116 and / or vanes 120 of the accelerator 106.
  • the mechanical part according to the present invention can also constitute the blades and / or mobiles of other elements of a turbojet engine, identical or different from that illustrated in FIG. a compressor, in particular a low pressure compressor.
  • the mechanical part according to the present invention can also find application in areas other than that of aeronautics for the formation of structural elements to resist mechanically while having a relatively light structure.
  • an aluminum rod 10 is first formed an aluminum rod 10 by conventional techniques for manufacturing aluminum alloys.
  • the next step is to introduce the rod 10 inside of the sleeve 20 to form an assembly 30: it is clear that at this stage it there is a clearance, or even a space between the outer surface of the rod 10 and the inner surface of the wall of the sleeve 20.
  • the assembly 30 appears to be introduced in the input 40 of a die 42.
  • This input 40 has a shape of truncated cone with an angle at the center ⁇ forming the angle of reduction.
  • This inlet 40 has an upstream diameter greater than the diameter outside the sleeve 20, while the downstream diameter of the inlet 40 has a diameter smaller than the diameter of the rod 10.
  • the assembly 30 is, during the passage in force and at the inlet 40 of the die 42, reduced in section by lengthening, an interface being created between the rod 10 and the sleeve 20 which together form in this way a complex semi-product 32 at the exit 44 of the die 42.
  • the reduction angle ⁇ is equal to 30 °, this reduction angle being able to vary in a general way between 1 ° and 45 ° and preferably between 5 and 35 °.
  • this spinning technique in particular when it is carried out by the successive passage in series dies, allows, by the pressure exerted between the surfaces in contact by friction, good cohesion between the materials constituting the core and the envelope.
  • This embodiment has been realized with a rod 10 having a diameter of 30 mm made of an aluminum alloy of 2024 T4 series, while the sleeve 20 had an outer diameter of 70 mm and an inside diameter of 40 mm being realized in a second material forming a metal matrix composite, the matrix metal alloy being a 2024 T4 series aluminum alloy and the reinforcement being composed of silicon carbide particles of a average size of 5 ⁇ m to 15% by weight.
  • Such spinning can be carried out at room temperature or hot, especially with a temperature of the order of 400 ° C.
  • the subsequent step of the exemplary embodiment described in detail is to perform forging by stamping to give the almost definitive shape of dawn.
  • This mastering is achieved by successive steps in matrices gradually tending to present the final shape of dawn under pressure and temperature conditions adapted to materials to maintain a good interface and good adhesion between the core and the envelope: a temperature of the order of 430 ° C and a pressure of the order of 100 MPa have been used in particular.
  • a blank (not shown) is obtained which is then machined to lead to a finished product forming the mechanical part according to the invention, in particular a blade such as those represented in Figures 3 to 5.
  • the blade 50 which is represented according to different shapes has a core 52 made of the first material initially constituting the rod 10, while the envelope 54 surrounding the core 52 is made in the second material initially forming the sleeve 20 of the assembly 30 of FIG.
  • dawn 50 has a regular distribution of the first material and the second material between the core 52 and the casing 54.
  • the present invention is not limited to the use of reinforcing elements in the form of silicon carbide particles, alumina particles (Al 2 O 3 ) or metal carbides, such as tungsten carbide, tungsten carbide, boron carbide or titanium carbide can also be used.
  • the present invention also applies to the production of a part mechanical made entirely of a metal matrix composite, which has a progressive composition of reinforcing elements from the center of the nucleus to the periphery of the envelope.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Powder Metallurgy (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
EP03291800A 2002-07-25 2003-07-21 Metallische Verbundschaufel und Verfahren ihrer Herstellung Expired - Lifetime EP1384539B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0209444A FR2842828B1 (fr) 2002-07-25 2002-07-25 Piece mecanique, et procede de fabrication d'une telle piece mecanique
FR0209444 2002-07-25

Publications (2)

Publication Number Publication Date
EP1384539A1 true EP1384539A1 (de) 2004-01-28
EP1384539B1 EP1384539B1 (de) 2010-02-10

Family

ID=29797665

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03291800A Expired - Lifetime EP1384539B1 (de) 2002-07-25 2003-07-21 Metallische Verbundschaufel und Verfahren ihrer Herstellung

Country Status (12)

Country Link
US (1) US7749342B2 (de)
EP (1) EP1384539B1 (de)
JP (1) JP2005533931A (de)
CN (1) CN1671498B (de)
AU (1) AU2003269058A1 (de)
CA (1) CA2493445C (de)
DE (1) DE60331206D1 (de)
ES (1) ES2340372T3 (de)
FR (1) FR2842828B1 (de)
RU (1) RU2347648C2 (de)
UA (1) UA82069C2 (de)
WO (1) WO2004011687A2 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7510778B2 (en) * 2005-04-15 2009-03-31 Snecma Part for protecting the leading edge of a blade
EP3460188A1 (de) * 2017-09-22 2019-03-27 Rolls-Royce plc Tragflügelbauteil und verfahren
WO2020007916A1 (en) * 2018-07-04 2020-01-09 Rolls-Royce Plc Method and tool set for manufacturing a composite component

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6701998B2 (en) * 2002-03-29 2004-03-09 Water Gremlin Company Multiple casting apparatus and method
US8701743B2 (en) 2004-01-02 2014-04-22 Water Gremlin Company Battery parts and associated systems and methods
US7338539B2 (en) 2004-01-02 2008-03-04 Water Gremlin Company Die cast battery terminal and a method of making
US7617582B2 (en) * 2005-07-05 2009-11-17 Honeywell International Inc. Method of manufacturing composite generator rotor shaft
WO2010127289A1 (en) 2009-04-30 2010-11-04 Water Gremlin Company Battery parts having retaining and sealing features and associated methods of manufacture and use
US8272085B2 (en) * 2009-10-13 2012-09-25 Justin Finch Boat hammock installation system
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
DE102010034014B4 (de) * 2010-08-11 2015-06-25 Schwäbische Hüttenwerke Automotive GmbH Sinterverbund und Verfahren zu seiner Herstellung
CN102455249B (zh) * 2010-11-03 2014-02-19 上海微电子装备有限公司 气浮轴承的刚度测试装置
US9748551B2 (en) 2011-06-29 2017-08-29 Water Gremlin Company Battery parts having retaining and sealing features and associated methods of manufacture and use
FR2982518B1 (fr) * 2011-11-15 2013-12-20 Snecma Conception d'une piece en materiau composite tisse 3d
US20130192982A1 (en) * 2012-02-01 2013-08-01 United Technologies Corporation Surface implantation for corrosion protection of aluminum components
FR2993577B1 (fr) * 2012-07-20 2016-03-11 Snecma Revetement abradable resistant a la corrosion
US9954214B2 (en) 2013-03-15 2018-04-24 Water Gremlin Company Systems and methods for manufacturing battery parts
RU2528926C1 (ru) * 2013-04-30 2014-09-20 Федеральное государственное бюджетное учреждение науки Институт машиноведения Уральского отделения Российской академии наук (ИМАШ УрО РАН) Способ получения металломатричного композиционного материала
FR3037097B1 (fr) * 2015-06-03 2017-06-23 Snecma Aube composite comprenant une plateforme munie d'un raidisseur
MX2021006454A (es) 2018-12-07 2021-07-02 Water Gremlin Co Partes de bateria que tienen barreras contra acidos sin solventes y sistemas y metodos asociados.

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0019569A1 (de) * 1979-05-16 1980-11-26 Cegedur Societe De Transformation De L'aluminium Pechiney Hohler Verbundkörper und Verfahren zur Herstellung
US4314007A (en) * 1976-08-26 1982-02-02 Bbc Brown, Boveri & Company Limited Composite shaped articles
DE4137839A1 (de) * 1991-11-16 1993-05-19 Asea Brown Boveri Verfahren zum anbringen einer erosionsschutzschicht
EP0809050A1 (de) * 1996-05-20 1997-11-26 Yamaha Hatsudoki Kabushiki Kaisha Kolben für eine Brennkraftmaschine und Verfahren zu ihrer Herstellung

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5662956A (en) * 1979-10-15 1981-05-29 United Technologies Corp Corrosion and abrasion resistant coating material
AU6744381A (en) * 1980-02-27 1981-09-03 British Internal Combustion Engine Research Institute Limited, The Sintered piston
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
JPH01180927A (ja) * 1988-01-13 1989-07-18 Toyota Motor Corp ピストン製造方法
GB2242848A (en) * 1990-04-12 1991-10-16 Frictec Ltd Depositing coating on materials
US5439750A (en) * 1993-06-15 1995-08-08 General Electric Company Titanium metal matrix composite inserts for stiffening turbine engine components
US6203897B1 (en) * 1993-09-24 2001-03-20 The Ishizuka Research Institute, Ltd. Sintered composites containing superabrasive particles
US5669059A (en) * 1994-01-19 1997-09-16 Alyn Corporation Metal matrix compositions and method of manufacturing thereof
US5490764A (en) * 1994-05-23 1996-02-13 General Electric Company Unshrouded blading for high bypass turbofan engines
US6190133B1 (en) * 1998-08-14 2001-02-20 Allison Engine Company High stiffness airoil and method of manufacture
FR2784616B1 (fr) * 1998-10-15 2000-11-17 Snecma Procede d'obtention de pieces metalliques minces, legeres et rigides
DE19859477B4 (de) * 1998-12-22 2005-06-23 Mtu Aero Engines Gmbh Verschleißschutzschicht
DE19959598A1 (de) * 1999-12-10 2001-06-13 Rolls Royce Deutschland Verfahren zum Herstellen einer Schaufel einer Strömungsmaschine
FR2884550B1 (fr) * 2005-04-15 2010-09-17 Snecma Moteurs Piece pour proteger le bord d'attaque d'une pale

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314007A (en) * 1976-08-26 1982-02-02 Bbc Brown, Boveri & Company Limited Composite shaped articles
EP0019569A1 (de) * 1979-05-16 1980-11-26 Cegedur Societe De Transformation De L'aluminium Pechiney Hohler Verbundkörper und Verfahren zur Herstellung
DE4137839A1 (de) * 1991-11-16 1993-05-19 Asea Brown Boveri Verfahren zum anbringen einer erosionsschutzschicht
EP0809050A1 (de) * 1996-05-20 1997-11-26 Yamaha Hatsudoki Kabushiki Kaisha Kolben für eine Brennkraftmaschine und Verfahren zu ihrer Herstellung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
QIN X H ET AL: "RESEARCH ON DISTRIBUTION OF SIC PARTICLES IN ALUMINUM-ALLOY MATRIX FUNCTIONALLY GRADED COMPOSITE TUBE MANUFACTURED BY CENTRIGUGAL CASTING", JOURNAL OF MATERIALS SCIENCE LETTERS, CHAPMAN AND HALL LTD. LONDON, GB, vol. 21, no. 8, 15 April 2002 (2002-04-15), pages 665 - 667, XP001125003, ISSN: 0261-8028 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7510778B2 (en) * 2005-04-15 2009-03-31 Snecma Part for protecting the leading edge of a blade
EP3460188A1 (de) * 2017-09-22 2019-03-27 Rolls-Royce plc Tragflügelbauteil und verfahren
WO2020007916A1 (en) * 2018-07-04 2020-01-09 Rolls-Royce Plc Method and tool set for manufacturing a composite component

Also Published As

Publication number Publication date
RU2005105069A (ru) 2005-07-20
US20060127693A1 (en) 2006-06-15
FR2842828A1 (fr) 2004-01-30
US7749342B2 (en) 2010-07-06
DE60331206D1 (de) 2010-03-25
RU2347648C2 (ru) 2009-02-27
CN1671498B (zh) 2010-09-01
EP1384539B1 (de) 2010-02-10
FR2842828B1 (fr) 2005-04-29
ES2340372T3 (es) 2010-06-02
AU2003269058A1 (en) 2004-02-16
CA2493445C (fr) 2011-06-14
CA2493445A1 (fr) 2004-02-05
AU2003269058A8 (en) 2004-02-16
CN1671498A (zh) 2005-09-21
JP2005533931A (ja) 2005-11-10
WO2004011687A2 (fr) 2004-02-05
WO2004011687A3 (fr) 2004-04-15
UA82069C2 (uk) 2008-03-11

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