FR3077224B1 - IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE - Google Patents

IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE Download PDF

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Publication number
FR3077224B1
FR3077224B1 FR1850871A FR1850871A FR3077224B1 FR 3077224 B1 FR3077224 B1 FR 3077224B1 FR 1850871 A FR1850871 A FR 1850871A FR 1850871 A FR1850871 A FR 1850871A FR 3077224 B1 FR3077224 B1 FR 3077224B1
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FR
France
Prior art keywords
alloy
cavity
blade
monocrystalline part
turbomachine
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
FR1850871A
Other languages
French (fr)
Other versions
FR3077224A1 (en
Inventor
Fabrice Crabos
Philippe Belaygue
Pierre Caron
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines 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 Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR1850871A priority Critical patent/FR3077224B1/en
Publication of FR3077224A1 publication Critical patent/FR3077224A1/en
Application granted granted Critical
Publication of FR3077224B1 publication Critical patent/FR3077224B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/16—Casting in, on, or around objects which form part of the product for making compound objects cast of two or more different metals, e.g. for making rolls for rolling mills
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/04—Casting in, on, or around objects which form part of the product for joining parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
    • B22D21/02—Casting exceedingly oxidisable non-ferrous metals, e.g. in inert atmosphere
    • B22D21/025—Casting heavy metals with high melting point, i.e. 1000 - 1600 degrees C, e.g. Co 1490 degrees C, Ni 1450 degrees C, Mn 1240 degrees C, Cu 1083 degrees C
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
    • B22D27/045—Directionally solidified castings
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
    • C30B29/10—Inorganic compounds or compositions
    • C30B29/52—Alloys
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Architecture (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé de fabrication d'une aube monocristalline pour turbomachine, comprenant une pale, un pied et une plateforme, et l'aube ayant une première portion, incluant la pale, en un premier alliage métallique, et une deuxième portion, incluant le pied, en un deuxième alliage métallique, les premier et deuxième alliages ayant des compositions chimiques différentes et le premier alliage étant plus dense que le deuxième alliage. Il comprend les étapes successives suivantes : -la réalisation d'une pièce monocristalline par coulée sous vide du premier alliage à l'état liquide dans une première cavité de moulage, suivie de la solidification dirigée du premier alliage du bas de la première cavité vers le haut, la pièce monocristalline ainsi obtenue incluant la première portion de l'aube à fabriquer ; - l'application d'un traitement thermique de mise en solution à la pièce monocristalline ; - l'extraction de la pièce monocristalline hors de la première cavité et son placement dans une deuxième cavité de moulage ; -la réalisation de l'aube par coulée sous vide du deuxième alliage à l'état liquide dans la deuxième cavité, suivie de la solidification dirigée du deuxième alliage du bas de la deuxième cavité vers le haut, la pièce monocristalline en premier alliage étant disposée dans la partie inférieure de la deuxième cavité et servant de germe à la solidification dirigée du deuxième alliage ; - l'application d'un traitement thermique de mise en solution à l'aube ; - l'extraction de l'aube hors de la deuxième cavité.The invention relates to a method of manufacturing a single crystal blade for a turbomachine, comprising a blade, a root and a platform, and the blade having a first portion, including the blade, in a first metal alloy, and a second portion, including the foot, of a second metal alloy, the first and second alloys having different chemical compositions and the first alloy being denser than the second alloy. It comprises the following successive steps: the production of a monocrystalline part by vacuum casting of the first alloy in the liquid state in a first molding cavity, followed by the directed solidification of the first alloy from the bottom of the first cavity towards the bottom. top, the monocrystalline part thus obtained including the first portion of the blade to be manufactured; - The application of a heat treatment of dissolution to the monocrystalline part; - Extracting the monocrystalline part from the first cavity and placing it in a second mold cavity; -the production of the blade by vacuum casting the second alloy in the liquid state in the second cavity, followed by the directed solidification of the second alloy from the bottom of the second cavity upwards, the monocrystalline part in the first alloy being placed in the lower part of the second cavity and serving as a seed for the directed solidification of the second alloy; - the application of a heat treatment to dissolve at dawn; - extracting the blade from the second cavity.

FR1850871A 2018-02-01 2018-02-01 IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE Active FR3077224B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1850871A FR3077224B1 (en) 2018-02-01 2018-02-01 IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1850871A FR3077224B1 (en) 2018-02-01 2018-02-01 IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE
FR1850871 2018-02-01

Publications (2)

Publication Number Publication Date
FR3077224A1 FR3077224A1 (en) 2019-08-02
FR3077224B1 true FR3077224B1 (en) 2021-10-08

Family

ID=62749075

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1850871A Active FR3077224B1 (en) 2018-02-01 2018-02-01 IMPROVED PROCESS FOR MANUFACTURING A MONOCRISTALLINE VANE FOR TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3077224B1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3105035B1 (en) * 2019-12-23 2021-12-10 Safran Helicopter Engines A method of manufacturing a turbomachine blade and a turbomachine blade
FR3127144A1 (en) * 2021-09-23 2023-03-24 Safran Process for manufacturing a bi-material aeronautical part
FR3141247A1 (en) 2022-10-20 2024-04-26 Safran PROCESS FOR MANUFACTURING SEVERAL BI-MATERIAL SPECIMENS

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9475119B2 (en) * 2012-08-03 2016-10-25 General Electric Company Molded articles
WO2014093826A2 (en) * 2012-12-14 2014-06-19 United Technologies Corporation Multi-shot casting
US10422228B2 (en) * 2016-04-12 2019-09-24 United Technologies Corporation Manufacturing a monolithic component with discrete portions formed of different metals

Also Published As

Publication number Publication date
FR3077224A1 (en) 2019-08-02

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