EP0700738A1 - Verfahren zur Herstellung einer hohlen Turbinenschaufel - Google Patents

Verfahren zur Herstellung einer hohlen Turbinenschaufel Download PDF

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Publication number
EP0700738A1
EP0700738A1 EP95402012A EP95402012A EP0700738A1 EP 0700738 A1 EP0700738 A1 EP 0700738A1 EP 95402012 A EP95402012 A EP 95402012A EP 95402012 A EP95402012 A EP 95402012A EP 0700738 A1 EP0700738 A1 EP 0700738A1
Authority
EP
European Patent Office
Prior art keywords
manufacturing
twisting
blade according
temperature
blade
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
EP95402012A
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English (en)
French (fr)
Other versions
EP0700738B1 (de
Inventor
Matthieu Bichon
Yvon Marie Joseph Louesdon
Charles Jean Pierre Douguet
Florence Anne Nathalie Renou
Alain Georges Henri Lorieux
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0700738A1 publication Critical patent/EP0700738A1/de
Application granted granted Critical
Publication of EP0700738B1 publication Critical patent/EP0700738B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • B21D26/055—Blanks having super-plastic properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/78—Making other particular articles propeller blades; turbine blades
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade

Definitions

  • the present invention relates to a method for manufacturing a hollow turbine engine blade.
  • EP-A-0.500.458 describes a method of manufacturing a hollow blade for a turbomachine, in particular a fan blade rotor with a large cord.
  • the primary parts used in this manufacture comprise two external sheets and at least one central sheet.
  • the described method comprises a hot forming operation by bending and twisting the parts, a welding-diffusion operation in localized areas and an inflation operation under gas pressure inducing a superplastic forming bringing the outer surfaces of the blade to the profile. research.
  • Appropriate tools, in particular shape dies, are used for carrying out these operations.
  • the object of the invention is to provide the numerous known methods for manufacturing hollow blades, illustrated in particular by the example cited above, substantial improvements aimed in particular at obtaining blades having improved and optimized mechanical characteristics in conditions of use, guaranteeing repetitive quality while facilitating manufacturing conditions at the lowest cost.
  • the grain size obtained is less than 10 ⁇ m, for a stamping temperature of the part comprised between 880 ° C. and 950 ° C. and a tooling temperature comprised between 600 ° C and 850 ° C.
  • the bending / twisting of the blades placed after the welding-diffusion operation allows greater ease of application of the diffusion barriers on a pre-established pattern on a flat part.
  • the production of a fan blade with a very high compression ratio presupposes a very strong camber of the pale base and an accentuated and non-continuous twist. This requires a specific fiber elongation operation before the twisting operation.
  • the twisting operation in this case can be integrated with the inflation operation under gas pressure and superplastic forming.
  • the operation of bending / twisting the blades can be placed after the forging operation in the case of exploratory development requiring small series of parts, or after the operation of machining the primary parts in the case of simple aerodynamic shapes.
  • the bending / twisting operation is carried out on a press, in an isothermal manner.
  • this temperature will be between 700 and 940 ° C.
  • This operation requires blocking of the ends in order to guarantee effective elongation of the fibers in the chosen areas, this without tearing.
  • the length of the central fiber remains unchanged and the rate of elongation of the fibers varies according to their distance from this central fiber.
  • the first step (a) of the process for manufacturing a hollow turbomachine fan blade according to the invention comprises a so-called flattening operation, from the definition of the finished part.
  • the flattening operation consists of deflation followed by defreezing / descaling.
  • the principles of construction and control of a fan blade are based on the use of defining sections distributed along the motor axis. Each section is worked so that all of the other constituent parts of the blade such as 11, 12 are pressed against the underside skin 13 unchanged. The thickness of the upper skin 11 is adjusted as a function of its subsequent elongation during the forming operation.
  • a digital simulation of the inflation is carried out confirming the intermediate result.
  • the second step (b) consists in forging on press the primary parts constituting the blade such as 11, 12, 13 visible in FIG. 9, by stamping. According to prior known techniques, this type of part is manufactured from laminated sheets because it is considered that the dimension and the size do not allow a sufficiently precise and fine blank to be ensured by forging.
  • the raw starting part consists, as shown in FIG. 2, of a bar 3, of a titanium alloy for example TA6V, of adequate size (diameter between 80 and 120mm) for roughing out the primary parts.
  • a bar 3 of a titanium alloy for example TA6V of adequate size (diameter between 80 and 120mm) for roughing out the primary parts.
  • one or more upsetting operations allow the material to be placed in areas of high volume, of the foot 4 or blade tip type.
  • the bars are heated to a temperature between 880 ° C and 950 ° C, while the tooling is heated to a temperature between 200 and 250 ° C.
  • a 270KN thrust class turbojet requires blades with a width of around 500 mm. This width is further increased by possible over widths of up to about 50 mm on each edge to perform functions of the product assembly, holding, etc. type.
  • the inventors have developed a process comprising a judicious combination of a trapezoidal shape 6 of l 'blank 5 as shown in Figure 4, the lubrication and heating of the tools.
  • the forging operation on a press or forging which makes it possible to obtain the parts such as 5 in FIG. 4 is carried out by heating the part to a temperature between 880 ° C. and 950 ° C. and the tooling to a temperature comprised between 700 ° C and 900 ° C.
  • Figure 7 shows a graph of temperature evolution at each stamping.
  • Curve a corresponds to the temperatures of the matrix contact surfaces
  • curve b the internal temperature of the tool
  • curve c the temperature of the tool holder. It can be seen that thanks to a perfectly controlled matrixing cycle, the temperature cycle varies between 720 ° C and 840 ° C.
  • the structure of the feeder bars 3 is coarse compared to the conventional specifications applied to bars of smaller dimensions (diameter 50 mm) used for the forging of conventional blades of a turbojet engine: forging and forging allow the structure of significantly since the grain size is reduced from 10 ⁇ m on average to 7 ⁇ m. This operation thus saves 30 MPa on average on the fatigue resistance of the final product and this despite the thermal cycles of welding-diffusion and inflation which follow the forging operation.
  • the forging precision makes it possible to finish the finished external left surface 8 of forging: the final surface condition being obtained by selective polishing, with numerical control, carried out on a polish 5 axes.
  • the internal surface 9 of the primary parts is finished by machining by any machining process known per se, these machining operations constituting step (C) of the process according to the invention.
  • stages (f) of inflation under gas pressure and superplastic forming and (g) final machining are then carried out under production conditions known per se, the parameters, in particular the temperature and the pressures applied being determined according to the material of the parts.
  • shaping of the parts by bending / twisting may be necessary.
  • the bending / twisting is a delicate operation which requires a certain number of precautions to avoid the appearance of undulations due to the lengthening of the different parts of the part during this operation.
  • the operation consists of isothermal shaping of the primary part or of the welded assembly, in a press at a temperature of between 700 and 940 ° C. allowing, with a tool 21, to obtain the elongations of the different fibers of the Exhibit 19.
  • This operation is carried out at controlled pressure between two metal or ceramic tools at the same temperature as the part is 700 ° C to 940 ° C.
  • the geometric definition of the tool 21 produced in CAD / CAM integrates the shape of the massive part of the foot 22 and laterally the progressive elongations of the fibers in particular by one or more waves 23, 24, 25, 26 whose amplitude varies with the rate d 'necessary extension, as shown schematically in Figures 13 and 14.
  • This operation may include bending the foot 22.
  • the addition of judiciously placed thickeners 28, 29, 30 makes it possible to maintain them from the first part / tool contact, as shown in FIG. 15.
  • the welded assembly 31 is held at each end by two jaws 32, 33 of which at least one is movable in rotation.
  • the twisting operation is carried out in an oven or a heating chamber, at a creep temperature between 880 ° C and 920 ° C depending on the alloy of the welded assembly.
  • Weights 34,35 impose on the part a twist perfectly controlled by limit stops.
  • another method is to provide the rotational movement of at least one of the jaws by a mechanical system acting on the lever arm 37, this is then carried out by two fingers fixed on the movable part of a press. which is added a local heating enclosure 38. Added local footprints 36 make it possible to obtain the accentuated aerodynamic shape of the trailing edge.
  • one of the jaws can be equipped with a helical coupling in order to apply to the part a tensile stress during the twisting, making it possible to avoid the appearance of a phenomenon of undulation, remarkably, in accordance with the invention.
  • the super plastic forming operation is carried out between 850 and 940 ° C under a pressure of 20 to 40x105MPa of argon.
  • the blade 31 is possible to form the blade 31 from the geometry obtained after elongation of the fibers in the same operation as the inflation.
  • the reduction in the number of heaters promotes the preservation of the high mechanical characteristics obtained by forging the component parts of the blade.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Powder Metallurgy (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95402012A 1994-09-07 1995-09-06 Verfahren zur Herstellung einer hohlen Turbinenschaufel Expired - Lifetime EP0700738B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9410690A FR2724127B1 (fr) 1994-09-07 1994-09-07 Procede de fabrication d'une aube creuse de turbomachine
FR9410690 1994-09-07

Publications (2)

Publication Number Publication Date
EP0700738A1 true EP0700738A1 (de) 1996-03-13
EP0700738B1 EP0700738B1 (de) 1999-12-08

Family

ID=9466749

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402012A Expired - Lifetime EP0700738B1 (de) 1994-09-07 1995-09-06 Verfahren zur Herstellung einer hohlen Turbinenschaufel

Country Status (9)

Country Link
US (1) US5636440A (de)
EP (1) EP0700738B1 (de)
JP (1) JP3305927B2 (de)
AT (1) ATE187370T1 (de)
CA (1) CA2157643C (de)
DE (1) DE69513754T2 (de)
ES (1) ES2139860T3 (de)
FR (1) FR2724127B1 (de)
IL (1) IL115123A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0765711A1 (de) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinenschaufel
EP0812649A1 (de) * 1996-06-13 1997-12-17 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Verfahren zur Herstellung einer hohlen Turbinenschaufel und mehrstufige Druckofen zur Durchführung des Verfahrens
EP0824048A1 (de) * 1996-08-14 1998-02-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zum Herstellen einer hohlen Turbinenschaufel mit Trennmaterial nach dem Schweissen
EP0824981A1 (de) * 1996-08-22 1998-02-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden
FR2754478A1 (fr) * 1996-10-16 1998-04-17 Snecma Procede de fabrication d'une aube creuse de turbomachine
EP2184119A2 (de) 2008-11-10 2010-05-12 Rolls-Royce plc Formungsvorrichtung
CN101773972A (zh) * 2010-02-25 2010-07-14 无锡透平叶片有限公司 一种高强铝合金坯料的制坯工艺
EP2295164A3 (de) * 2009-09-11 2014-12-17 Rolls-Royce plc Umformwerkzeug
CN105290380A (zh) * 2015-11-12 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 一种定向凝固叶片浇注系统用内置挡板的设计方法
CN105404759A (zh) * 2015-12-25 2016-03-16 鼎奇(天津)主轴科技有限公司 一种焊接结构件的三维或二维设计方法

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6129261A (en) * 1996-09-26 2000-10-10 The Boeing Company Diffusion bonding of metals
JP3647612B2 (ja) * 1997-07-24 2005-05-18 富士重工業株式会社 航空機の前縁構造及びその製造方法
US6264880B1 (en) 1998-07-22 2001-07-24 The Regents Of The University Of California Manifold free multiple sheet superplastic forming
US6223573B1 (en) * 1999-06-25 2001-05-01 General Electric Company Method for precision temperature controlled hot forming
GB2360236B (en) * 2000-03-18 2003-05-14 Rolls Royce Plc A method of manufacturing an article by diffusion bonding and superplastic forming
US6792655B2 (en) * 2001-11-09 2004-09-21 General Electric Company Apparatus for correcting airfoil twist
GB0203955D0 (en) 2002-02-20 2002-04-03 Rolls Royce Plc A method of manufacturing an article by diffusion bonding and super[lastic forming
US6705011B1 (en) 2003-02-10 2004-03-16 United Technologies Corporation Turbine element manufacture
FR2855439B1 (fr) * 2003-05-27 2006-07-14 Snecma Moteurs Procede de fabrication d'une aube creuse pour turbomachine.
FR2857889B1 (fr) * 2003-07-23 2005-09-23 Snecma Moteurs Procede de fabrication de pieces par forgeage de precision
FR2867095B1 (fr) * 2004-03-03 2007-04-20 Snecma Moteurs Procede de fabrication d'une aube creuse pour turbomachine.
FR2867096B1 (fr) * 2004-03-08 2007-04-20 Snecma Moteurs Procede de fabrication d'un bord d'attaque ou de fuite de renforcement pour une aube de soufflante
FR2871397B1 (fr) * 2004-06-11 2006-09-22 Snecma Moteurs Sa Installation de conformation d'une aube creuse
FR2872721B1 (fr) * 2004-07-09 2006-09-22 Snecma Moteurs Sa Procede de construction geometrique d'un cordon de bavure de forgeage de piece complexe
FR2873940B1 (fr) * 2004-08-03 2008-01-04 Snecma Moteurs Sa Procede de fabrication de pieces constitutives d'une aube creuse par laminage
FR2874339B1 (fr) * 2004-08-23 2008-12-05 Snecma Moteurs Sa Procede de fabrication de pieces constitutives d'une aube creuse par forage sur presse
DE102004062174A1 (de) * 2004-12-17 2006-06-22 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung von hoch belastbaren Bauteilen durch Präzisionsschmieden
JP5297047B2 (ja) * 2008-01-18 2013-09-25 三菱重工業株式会社 ポンプの性能特性設定方法およびディフューザベーンの製造方法
EA016027B1 (ru) * 2008-10-13 2012-01-30 Государственное Научное Учреждение "Физико-Технический Институт Национальной Академии Наук Беларуси" Способ формообразования поковки штифта эндопротеза тазобедренного сустава
RU2412017C2 (ru) * 2008-12-24 2011-02-20 ОАО "Авиадвигатель" Способ изготовления полой вентиляторной лопатки
CN101658895B (zh) * 2009-03-19 2011-06-22 无锡透平叶片有限公司 航空发动机ta19钛合金机匣厚板局部加载成形方法
US20120096915A1 (en) * 2010-10-25 2012-04-26 General Electric Company System and method for near net shape forging
FR2978926B1 (fr) * 2011-08-11 2014-05-09 Snecma Dispositif pour la mise en forme d'une tole par matricage
DE102011082850A1 (de) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Verdichterschaufel und Verfahren zu ihrer Herstellung
JP5702710B2 (ja) * 2011-12-21 2015-04-15 株式会社日立製作所 自由鍛造方法及び鍛造装置
ITCO20120059A1 (it) * 2012-12-13 2014-06-14 Nuovo Pignone Srl Metodi per produrre pale cave sagomate in 3d di turbomacchine mediante produzione additiva, pale cave di turbomacchina e turbomacchine
RU2525010C1 (ru) * 2012-12-20 2014-08-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Заготовка для изготовления полой лопатки турбомашины способом сверхпластической формовки
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JP6206739B2 (ja) * 2013-10-01 2017-10-04 日立金属株式会社 タービンブレードの製造方法
RU2548834C1 (ru) * 2013-10-03 2015-04-20 Федеральное государственное бюджетное учреждение науки Институт проблем сверхпластичности металлов Российской академии наук (ИПСМ РАН) Способ изготовления полого изделия типа вентиляторной лопатки
CN106734820B (zh) * 2016-12-29 2019-05-03 无锡透平叶片有限公司 一种汽轮机叶片坯料的定位装置
CN109210001B (zh) * 2017-07-13 2019-07-09 中国航空制造技术研究院 一种超塑成形空心扭转叶片的设计方法
CN107838642B (zh) * 2017-12-18 2019-03-05 中国航发贵州黎阳航空动力有限公司 一种双轴颈薄壁叶片零件的加工方法
CN108372391A (zh) * 2018-03-05 2018-08-07 广汉天空动力机械有限责任公司 一种涡轮转子空心叶片的制造方法
US11148221B2 (en) * 2019-08-29 2021-10-19 Raytheon Technologies Corporation Method of forming gas turbine engine components
CN115570105B (zh) * 2022-11-21 2023-05-05 中国航发四川燃气涡轮研究院 一种双层壁涡轮叶片的制造方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1291927A (en) * 1969-07-17 1972-10-04 Gen Electric Improvements in method for making a contoured article
EP0245548A1 (de) * 1985-04-15 1987-11-19 Ontario Technologies Corporation Herstellungsverfahren für eine hohle Metallstruktur vom Typ einer Tragfläche
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
EP0500458A1 (de) 1991-02-20 1992-08-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine
EP0568201A1 (de) * 1992-05-01 1993-11-03 ROLLS-ROYCE plc Verfahren zur Herstellung eines Gegenstandes durch superplastische Formung und Diffusionsschweissung
US5285573A (en) * 1991-12-09 1994-02-15 General Electric Company Method for manufacturing hollow airfoils (four-piece concept)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5063662A (en) * 1990-03-22 1991-11-12 United Technologies Corporation Method of forming a hollow blade
US5099573A (en) * 1990-06-27 1992-03-31 Compressor Components Textron Inc. Method of making hollow articles
US5083371A (en) * 1990-09-14 1992-01-28 United Technologies Corporation Hollow metal article fabrication

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1291927A (en) * 1969-07-17 1972-10-04 Gen Electric Improvements in method for making a contoured article
EP0245548A1 (de) * 1985-04-15 1987-11-19 Ontario Technologies Corporation Herstellungsverfahren für eine hohle Metallstruktur vom Typ einer Tragfläche
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
EP0500458A1 (de) 1991-02-20 1992-08-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine
US5285573A (en) * 1991-12-09 1994-02-15 General Electric Company Method for manufacturing hollow airfoils (four-piece concept)
EP0568201A1 (de) * 1992-05-01 1993-11-03 ROLLS-ROYCE plc Verfahren zur Herstellung eines Gegenstandes durch superplastische Formung und Diffusionsschweissung

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0765711A1 (de) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinenschaufel
EP0812649A1 (de) * 1996-06-13 1997-12-17 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Verfahren zur Herstellung einer hohlen Turbinenschaufel und mehrstufige Druckofen zur Durchführung des Verfahrens
FR2749784A1 (fr) * 1996-06-13 1997-12-19 Snecma Procede de fabrication d'un aube creuse de turbomachine et presse-four a multiple effet utilisee dans sa mise en oeuvre
US6210630B1 (en) 1996-06-13 2001-04-03 Societe Nationale d'Etude et de Construction de Monteurs d'Aviation “Snecma” Process for manufacturing a hollow turbomachine blade and a multiple-action furnace press for use in said process
US5933951A (en) * 1996-06-13 1999-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for manufacturing a hollow turbomachine blade and a multiple-action furnace press for use in said process
EP0824048A1 (de) * 1996-08-14 1998-02-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zum Herstellen einer hohlen Turbinenschaufel mit Trennmaterial nach dem Schweissen
FR2752388A1 (fr) * 1996-08-14 1998-02-20 Snecma Procede de fabrication d'une aube creuse de turbomachine comportant un decollement apres soudage
US5946802A (en) * 1996-08-14 1999-09-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for the manufacture of a hollow turbomachine blade and apparatus for use in said process
US5933952A (en) * 1996-08-22 1999-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for manufacturing a hollow turbomachine blade and progressive hot twisting apparatus for use in said process
FR2752539A1 (fr) * 1996-08-22 1998-02-27 Snecma Procede de fabrication d'une aube creuse de turbomachine et equipement de vrillage evolutif a chaud utilise
EP0824981A1 (de) * 1996-08-22 1998-02-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinschaufel und Anlage zum laufenden Warmverwinden
US6242715B1 (en) 1996-08-22 2001-06-05 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Progressive hot twisting apparatus for use in a process for manufacturing a hollow turbomachine blade
US5896658A (en) * 1996-10-16 1999-04-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method of manufacturing a hollow blade for a turbomachine
EP0836899A1 (de) * 1996-10-16 1998-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinenschaufel
FR2754478A1 (fr) * 1996-10-16 1998-04-17 Snecma Procede de fabrication d'une aube creuse de turbomachine
EP2184119A2 (de) 2008-11-10 2010-05-12 Rolls-Royce plc Formungsvorrichtung
EP2184119A3 (de) * 2008-11-10 2013-07-10 Rolls-Royce plc Formungsvorrichtung
US9010166B2 (en) 2008-11-10 2015-04-21 Rolls-Royce Plc Forming apparatus
EP2295164A3 (de) * 2009-09-11 2014-12-17 Rolls-Royce plc Umformwerkzeug
CN101773972A (zh) * 2010-02-25 2010-07-14 无锡透平叶片有限公司 一种高强铝合金坯料的制坯工艺
CN105290380A (zh) * 2015-11-12 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 一种定向凝固叶片浇注系统用内置挡板的设计方法
CN105290380B (zh) * 2015-11-12 2017-07-04 沈阳黎明航空发动机(集团)有限责任公司 一种定向凝固叶片浇注系统用内置挡板的设计方法
CN105404759A (zh) * 2015-12-25 2016-03-16 鼎奇(天津)主轴科技有限公司 一种焊接结构件的三维或二维设计方法

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Publication number Publication date
FR2724127A1 (fr) 1996-03-08
CA2157643C (fr) 2004-11-23
DE69513754T2 (de) 2000-06-29
IL115123A (en) 1999-11-30
FR2724127B1 (fr) 1996-12-20
ES2139860T3 (es) 2000-02-16
DE69513754D1 (de) 2000-01-13
ATE187370T1 (de) 1999-12-15
CA2157643A1 (fr) 1996-03-08
US5636440A (en) 1997-06-10
EP0700738B1 (de) 1999-12-08
JP3305927B2 (ja) 2002-07-24
IL115123A0 (en) 1995-12-31
JPH08189303A (ja) 1996-07-23

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