EP0500458B1 - Procédé de fabrication d'une aube creuse pour turbomachine - Google Patents

Procédé de fabrication d'une aube creuse pour turbomachine Download PDF

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Publication number
EP0500458B1
EP0500458B1 EP19920400435 EP92400435A EP0500458B1 EP 0500458 B1 EP0500458 B1 EP 0500458B1 EP 19920400435 EP19920400435 EP 19920400435 EP 92400435 A EP92400435 A EP 92400435A EP 0500458 B1 EP0500458 B1 EP 0500458B1
Authority
EP
European Patent Office
Prior art keywords
central
manufacturing
members
hollow blade
diffusion
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.)
Expired - Lifetime
Application number
EP19920400435
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0500458A1 (fr
Inventor
André Claude Félix Collot
Bernard Philippe Cornil Sohier
Danilo Varela
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 EP0500458A1 publication Critical patent/EP0500458A1/fr
Application granted granted Critical
Publication of EP0500458B1 publication Critical patent/EP0500458B1/fr
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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

Definitions

  • the present invention relates to a method of manufacturing a hollow blade for a turbomachine.
  • FR-A-1 577 388 gives an exemplary embodiment of a blade made up of two wall elements between which is disposed a honeycomb structure, these wall elements being made in particular of titanium alloy and being formed in profile and to the desired shape by hot pressing.
  • FR-A-2 286 688 and FR-A-2 304 438 is a method of producing a metal structure from several parts comprising a superplasticity forming operation, at high temperature, by applying the pressure d '' an inert fluid in a suitable tool, associated with diffusion welding.
  • US-A-4,882,823 which document is considered to be the closest state of the art, further describes a method of manufacturing a hollow part from at least two assembled sheets comprising the steps of setting place of diffusion, welding-diffusion and superplastic forming barriers by inflation in a tool.
  • a variant applicable to turbomachine blades provides after the diffusion diffusion of the structure an operation of shaping the blade by twisting before performing the superplastic forming.
  • the object of the invention is to apply to the production of parts having a structure with at least three sheets and having if necessary a controlled distribution of the masses with respect to a centrifugal field in the case of parts rotating, an alternative method of manufacturing process allowing in particular to obtain fan blades with a large cord.
  • a single central sheet or two central sheets can be used.
  • the outer sheets can be obtained by hot forming from parts with decreasing thickness or by forming / pushing back using methods known per se of matrix forging. hot or isothermal forging.
  • the central sheet (s) can be chemically machined, either at the primary part stage in stage (a) of the process, or after stage (b) before installation diffusion barriers.
  • FIG. 1 shows an example of two external sheets 1 equipped with pins 2, and d 'a central sheet 7 constituting the primary parts of the blade.
  • the method of manufacturing these primary parts uses techniques known per se.
  • Figure 1 shows said parts 1 and 7 after a bending / twisting operation according to a known hot forming technique using a tool not shown in the drawings.
  • a chemical machining operation can be carried out on the central sheet 7 in order to obtain a determined distribution of the masses on the blade by controlling the thicknesses.
  • FIGS. 3A and 3B represent said sheet 7 after chemical machining by showing sections in a direction perpendicular to the edges of the blade to be obtained or in a direction parallel to these edges.
  • Said central sheet 7 is then coated with diffusion barriers delimiting welding zones 12, as shown in FIG. 4.
  • the zones of application of diffusion barriers are delimited using a mask which can be either a tool rigid or flexible, or an adherent deposit on the surface of a suitable material known per se, which will be cut or peeled, constituting a diffusion barrier during welding and unmasking.
  • Figure 6 shows schematically the establishment of the blade vane 11 on a tool 14 which includes inlets 15 for pressurizing gas and suitable sealing devices.
  • the seal between inside and outside of the tool is produced by a separate seal 16 and the seal between the inside of the blade and the inside of the tool is ensured by means of a peripheral weld of the part, as indicated in 13 in FIG. 5.
  • the seals on the one hand of the tool with respect to the outside and, on the other hand from the inside of the blade relative to the inside of the tool can be provided using a seal produced directly by creep and welding-diffusion of the external contour of the part. In this case, the seal footprint will be eliminated during finishing by machining.
  • the welding-diffusion operation is carried out in the oven.
  • the operation is carried out at a temperature of 930 ° C. and a neutral gas, such as argon, is used to obtain the pressurization of the parts as shown by the arrows 17.
  • a neutral gas such as argon
  • the pressure applied is 4 MPa.
  • the welds 18 between the central sheet 7 and the external sheets 1 are arranged alternately on one side and the other, as shown in FIG. 6.
  • the blade 11 is then held in place on the single tool 14 to carry out the inflation operation and superplastic forming under argon pressure using the gas collector which has been previously set up and the gas inlets arranged during of the previous operation of chemical machining of the central sheet 7 and during the installation of the blade 11 on the tool 14.
  • the blade 11 during this operation thus takes its final internal shape as shown in figure 7.
  • two central sheets can be used so as to obtain a blade structure as shown diagrammatically in section in FIG. 8 where the external sheets 1 are associated with two central sheets 19 and 20.
  • other structures can be sought as shown in FIG. 9.
  • an operation of inflation under gas pressure and superplastic forming is also applied, in accordance with the invention, after the assembly has been subjected to a bending / twisting operation.
  • the proposed solution optionally makes it possible to use a different material for the central sheets and for the outer sheets whose material may, in particular, not have the same superplasticity properties as that of the central sheets.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19920400435 1991-02-20 1992-02-19 Procédé de fabrication d'une aube creuse pour turbomachine Expired - Lifetime EP0500458B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9102007A FR2672826B1 (fr) 1991-02-20 1991-02-20 Procede de fabrication d'une aube creuse pour turbomachine.
FR9102007 1991-02-20

Publications (2)

Publication Number Publication Date
EP0500458A1 EP0500458A1 (fr) 1992-08-26
EP0500458B1 true EP0500458B1 (fr) 1995-10-04

Family

ID=9409907

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19920400435 Expired - Lifetime EP0500458B1 (fr) 1991-02-20 1992-02-19 Procédé de fabrication d'une aube creuse pour turbomachine

Country Status (4)

Country Link
EP (1) EP0500458B1 (ja)
JP (1) JP2574589B2 (ja)
DE (1) DE69205187T2 (ja)
FR (1) FR2672826B1 (ja)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5243758A (en) * 1991-12-09 1993-09-14 General Electric Company Design and processing method for manufacturing hollow airfoils (three-piece concept)
US5469618A (en) * 1993-12-06 1995-11-28 General Electric Company Method for manufacturing hollow airfoils (two-piece concept)
FR2724127B1 (fr) 1994-09-07 1996-12-20 Snecma Procede de fabrication d'une aube creuse de turbomachine
FR2739045B1 (fr) * 1995-09-27 1997-10-31 Snecma Procede de fabrication d'une aube creuse de turbomachine
FR2739832B1 (fr) * 1995-10-12 1997-12-26 Aerospatiale Structure metallique creuse monobloc et dissymetrique telle qu'un bord de fuite d'un bec d'attaque d'une voilure d'aeronef et son procede de fabrication
FR2752388B1 (fr) * 1996-08-14 1998-09-18 Snecma Procede de fabrication d'une aube creuse de turbomachine comportant un decollement apres soudage
GB0522121D0 (en) * 2005-10-29 2005-12-07 Rolls Royce Plc A blade
EP1832714A1 (de) * 2006-03-06 2007-09-12 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Turbinen- oder Verdichterkomponente sowie Turbinen- oder Verdichterkomponente
KR100843448B1 (ko) * 2007-03-20 2008-07-03 현대중공업 주식회사 진동 감쇄형 익형 날개
GB2450934B (en) 2007-07-13 2009-10-07 Rolls Royce Plc A Component with a damping filler
WO2009039282A1 (en) * 2007-09-19 2009-03-26 Barnes Group Diffusion bonding
GB0808840D0 (en) 2008-05-15 2008-06-18 Rolls Royce Plc A compound structure
GB2462102B (en) 2008-07-24 2010-06-16 Rolls Royce Plc An aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US9289816B2 (en) * 2009-01-22 2016-03-22 Ihi Corporation Production method of leading edge reinforcement of fan blade
GB0901235D0 (en) 2009-01-27 2009-03-11 Rolls Royce Plc An article with a filler
GB0901318D0 (en) 2009-01-28 2009-03-11 Rolls Royce Plc A method of joining plates of material to form a structure
GB0911416D0 (en) * 2009-07-02 2009-08-12 Rolls Royce Plc A method of forming an internal structure within a hollow component
GB201009216D0 (en) 2010-06-02 2010-07-21 Rolls Royce Plc Rotationally balancing a rotating part
GB2485831B (en) 2010-11-26 2012-11-21 Rolls Royce Plc A method of manufacturing a component
JP6104725B2 (ja) * 2013-06-12 2017-03-29 三菱重工業株式会社 板状ワークの捩り保持装置および捩り保持方法ならびに捩り成形方法
CN113523728B (zh) * 2021-08-04 2023-01-03 哈尔滨汽轮机厂有限责任公司 一种空心导叶片的特种加工方法
CN113857346B (zh) * 2021-09-26 2024-01-09 北京航空航天大学 一种空心叶片热成型方法及空心叶片充气装置

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4642863A (en) * 1985-04-15 1987-02-17 Ontario Technologies Corporation Manufacturing method for hollow metal airfoil type structure
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
FR2647373B1 (fr) * 1989-05-26 1993-12-17 Dassault Breguet Aviation Procede de formage par deformation par pression de fluide

Also Published As

Publication number Publication date
FR2672826B1 (fr) 1995-04-21
EP0500458A1 (fr) 1992-08-26
FR2672826A1 (fr) 1992-08-21
JPH05192729A (ja) 1993-08-03
JP2574589B2 (ja) 1997-01-22
DE69205187T2 (de) 1996-04-04
DE69205187D1 (de) 1995-11-09

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