CA2467846A1 - Method of manufacturing a hollow blade for a turbine engine - Google Patents

Method of manufacturing a hollow blade for a turbine engine Download PDF

Info

Publication number
CA2467846A1
CA2467846A1 CA002467846A CA2467846A CA2467846A1 CA 2467846 A1 CA2467846 A1 CA 2467846A1 CA 002467846 A CA002467846 A CA 002467846A CA 2467846 A CA2467846 A CA 2467846A CA 2467846 A1 CA2467846 A1 CA 2467846A1
Authority
CA
Canada
Prior art keywords
preform
blade
manufacturing
additional element
unit
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
CA002467846A
Other languages
French (fr)
Other versions
CA2467846C (en
Inventor
Jean-Pierre Ferte
Jean-Michel Patrick Maurice Franchet
Daniel Gaston Lhomme
Alain 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
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of CA2467846A1 publication Critical patent/CA2467846A1/en
Application granted granted Critical
Publication of CA2467846C publication Critical patent/CA2467846C/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Forging (AREA)

Abstract

The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of a blade preform (14) bearing a rotor blade part and a foot part, this production stage of the blade preform comprising the following operations: - the making of a unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, in such a way that they solely form the rotor blade part of the preform; - the making of an additional element (34) intended to wholly form the foot part of the preform; and - the assembling of the additional element to the unit so as to obtain the blade preform.

Claims (4)

1. Method of manufacturing a hollow blade (1) for turbine engine comprising a foot (2) and a rotor blade (4), said method comprising a production stage of the blade preform (14) bearing a rotor blade part (18) and a foot part (16), the production stage of the preform (14) being performed in such a way that it comprises a unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, characterised in that the production stage of said blade preform (14) comprises the following operations:

- the making of said unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, in such a way that they solely form said rotor blade part (18) of the preform (14);

- the making of an additional element (34) intended to wholly form said foot part (16) of the preform (14); and - the assembling of the additional element (34) to the unit (28) so as to obtain said blade preform (14).
2. Manufacturing method set forth in claim 1, characterised in that the assembling operation of the additional element (34) to said unit (28) is implemented using a technique taken from among the group constituted of linear friction welding and of friction stir welding.
3. Manufacturing method set forth in claim 1 or claim 2, characterised in that the manufacturing stage of the blade preform (14) is followed by the following stages:

- airfoil profiling of said preform (14); and - bulging via gas pressure and superplastic forming of said airfoil profiling preform (14).
4. Manufacturing method set forth in any one of the previous claims, characterised in that the additional element (34) intended to wholly form said foot part (16) of the preform (14) is made via extrusion.
CA2467846A 2003-05-27 2004-05-19 Method of manufacturing a hollow blade for a turbine engine Expired - Lifetime CA2467846C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350185A FR2855440B1 (en) 2003-05-27 2003-05-27 METHOD FOR MANUFACTURING A HOLLOW DAWN FOR TURBOMACHINE
FR0350185 2003-05-27

Publications (2)

Publication Number Publication Date
CA2467846A1 true CA2467846A1 (en) 2004-11-27
CA2467846C CA2467846C (en) 2011-07-19

Family

ID=33104533

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2467846A Expired - Lifetime CA2467846C (en) 2003-05-27 2004-05-19 Method of manufacturing a hollow blade for a turbine engine

Country Status (8)

Country Link
EP (1) EP1481755B1 (en)
JP (1) JP4130423B2 (en)
CA (1) CA2467846C (en)
DE (1) DE602004020422D1 (en)
ES (1) ES2323461T3 (en)
FR (1) FR2855440B1 (en)
RU (1) RU2338886C2 (en)
UA (1) UA83793C2 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8016561B2 (en) * 2006-07-11 2011-09-13 General Electric Company Gas turbine engine fan assembly and method for assembling to same
JP4757750B2 (en) * 2006-09-11 2011-08-24 パナソニック株式会社 Imaging device
CA2719817C (en) 2008-03-28 2014-05-06 Ihi Corporation Gas turbine engine blade for aircraft and manufacturing method thereof
FR2953430B1 (en) * 2009-12-03 2012-03-02 Snecma PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT
US8905707B2 (en) * 2010-12-21 2014-12-09 Hamilton Sundstrand Corporation Bearing cooling control in an air cycle machine
CN105736462B (en) * 2014-12-12 2018-03-06 中国航发商用航空发动机有限责任公司 hollow blade and aero-engine
FR3035678B1 (en) * 2015-04-29 2017-05-12 Snecma DAWN WITH PLATFORMS HAVING A RESTRAINT LEG
FR3063663B1 (en) 2017-03-13 2021-02-26 Mecachrome France PROCESS FOR MANUFACTURING COMPLEX SHAPED METAL ALLOY PARTS
CN114700599B (en) * 2022-05-18 2023-02-28 中国航空制造技术研究院 Blade based on discharge plasma diffusion welding

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH238023A (en) * 1943-07-31 1945-06-15 Sulzer Ag Turbomachine blades and processes for their manufacture
FR970578A (en) * 1948-08-19 1951-01-05 Bohler & Cie Ag Geb Hollow blades for turbines, in particular for gas turbines, and method for their manufacture
US2767460A (en) * 1950-02-08 1956-10-23 Robbins Engineering Company Turbine blade and method of making same
GB789659A (en) * 1956-08-31 1958-01-22 Gen Motors Corp Improvements relating to the manufacture of metal blades having curved surfaces
US3982854A (en) * 1971-12-20 1976-09-28 General Electric Company Friction welded metallic turbomachinery blade element
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
US5469618A (en) * 1993-12-06 1995-11-28 General Electric Company Method for manufacturing hollow airfoils (two-piece concept)
GB0022531D0 (en) * 2000-09-14 2000-11-01 Rolls Royce Plc A method of manufacturing an article by diffusion bonding
US6537682B2 (en) * 2001-03-27 2003-03-25 The Boeing Company Application of friction stir welding to superplastically formed structural assemblies

Also Published As

Publication number Publication date
DE602004020422D1 (en) 2009-05-20
ES2323461T3 (en) 2009-07-16
UA83793C2 (en) 2008-08-26
RU2338886C2 (en) 2008-11-20
FR2855440B1 (en) 2006-07-14
EP1481755A1 (en) 2004-12-01
EP1481755B1 (en) 2009-04-08
FR2855440A1 (en) 2004-12-03
JP2004353666A (en) 2004-12-16
RU2004116118A (en) 2006-01-10
CA2467846C (en) 2011-07-19
JP4130423B2 (en) 2008-08-06

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