WO2004053181A2 - Procede pour produire un composant presentant une meilleure aptitude au soudage et/ou une meilleure aptitude a l'usinage mecanique a partir d'un alliage - Google Patents

Procede pour produire un composant presentant une meilleure aptitude au soudage et/ou une meilleure aptitude a l'usinage mecanique a partir d'un alliage Download PDF

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Publication number
WO2004053181A2
WO2004053181A2 PCT/EP2003/013882 EP0313882W WO2004053181A2 WO 2004053181 A2 WO2004053181 A2 WO 2004053181A2 EP 0313882 W EP0313882 W EP 0313882W WO 2004053181 A2 WO2004053181 A2 WO 2004053181A2
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WO
WIPO (PCT)
Prior art keywords
heat treatment
component
welding
alloy
carried out
Prior art date
Application number
PCT/EP2003/013882
Other languages
German (de)
English (en)
Other versions
WO2004053181A3 (fr
Inventor
Nigel-Philip Cox
Rolf WILKENHÖNER
Dirk Goldschmidt
Konstantin A. Yushchenko
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP03782329A priority Critical patent/EP1570098A2/fr
Priority to US10/538,414 priority patent/US20060144477A1/en
Priority to CN200380105754.3A priority patent/CN1726297B/zh
Publication of WO2004053181A2 publication Critical patent/WO2004053181A2/fr
Publication of WO2004053181A3 publication Critical patent/WO2004053181A3/fr

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Definitions

  • the invention relates to a method for producing a component with improved weldability and / or mechanical machinability from an alloy.
  • US Pat. No. 5,938,863 discloses a nickel-based superalloy which has additions of carbides in order to improve the fatigue behavior.
  • US Pat. No. 6,120,624 discloses heat treatment of a nickel-base superalloy before welding in order to avoid cracking during heat treatments after welding.
  • U.S. Patent 4,579,602 and U.S. Patent 4,574,015 disclose heat treatments for cast superalloys to improve the forging of these materials.
  • the component During the production of a component from an alloy, the component must be processed in various intermediate production steps.
  • the alloy often does not have the desired properties in order to process it optimally.
  • the alloy can be relatively brittle, making mechanical processing (straightening, machining, grinding) difficult.
  • the object is achieved by a method for producing a component with improved weldability and / or mechanical machinability from an alloy according to claim 1.
  • Figure 1 exemplary temporal profiles of the temperature of an alloy during a manufacturing process
  • Figure 3 different microstructures of an alloy.
  • FIG. 2 shows an exemplary time course of the temperature of an alloy during the manufacturing process.
  • the alloy can be hardened, for example, by precipitates, such as an iron, nickel or cobalt-based superalloy.
  • the alloy can be sintered into a component from a powder or cast as a melt or can also be solidified in a directed manner. Other types of production are conceivable.
  • the temperature is greater than the melting temperature Tiiquidus-
  • the melt is poured off (left area in the figure) and then more or less controlled slow or uncontrolled cooled so that the temperature below the solidus T is so u mode. Then the component has solidified.
  • the component is cooled, for example, to room temperature (intersection of the temperature axis T with the time axis t).
  • the casting process is followed, for example, not necessarily by post-compaction, in particular directly after the casting process, i.e. without cooling the component after casting.
  • the post-compression is carried out, for example, by hot isostatic pressing (HIP) (area I, Fig. 2) or possibly also by sintering in order to avoid errors such as e.g. Close pores, cavities, ..
  • the post-compaction can also be carried out after other manufacturing steps, for example after welding.
  • the temperature during the recompression (for example HIP) is below the solidus line T sol i dus of the alloy of the component.
  • the components made of this alloy are mechanically processed (for example, straightened or machined, grinding)
  • a subsequent improvement heat treatment according to the invention which leads, for example, to coarsening of the precipitates, for example by means of an aging heat treatment which leads to an aging of the structure of the alloy, changes the microstructure (structure) of the component in such a way that the processability of the alloy compared to the untreated one Structure is improved.
  • the structural features include the crystal structure, precipitations and secondary phases.
  • the exemplary aging heat treatment can be connected directly to the post-compression process, in particular in the same furnace, or after casting or sintering. There is no (FIG. 2, transition area I, II) or only an insignificant cooling of the component. If the post-compression process is carried out using a HIP process, the pressure during the improvement heat treatment can remain, be slowly reduced or reduced.
  • a holding time at the temperature for the improvement heat treatment can be omitted or reduced here, since this has already been done at least partially or entirely by the holding time for the HIP post-treatment.
  • the aging heat treatment is possibly after a holding time at a temperature by a low cooling rate of greater than or equal to 2 ° C to 5 ° C per minute, in particular from 2 ° C to 3 ° C per minute, in particular 2.33 ° C / min., Directly after After compression process reached (area II, Fig. 2).
  • Figure 1 shows the time course when the component is removed from the hot isostatic press and transported to another furnace.
  • the aging heat treatment is carried out by heating up to a certain temperature, possibly with a holding time at this temperature (heating up is not necessary in the process according to FIG. 2), and for example by a low cooling rate of greater than or equal to 2 ° C. to 5 ° C. per minute, in particular of 2 ° C to 3 ° C per minute, especially 2.33 ° C / min. (Area II, Fig.l) reached.
  • An aging heat treatment for IN738LC which also leads to coarsening of the excretions, has the following parameters, for example:
  • the holding temperature is 1204 ° C +/- 15 ° C.
  • the holding temperatures for the aging heat treatment are also the HIP temperatures, for example. But they can be higher or lower.
  • the aging heat treatment causes the ⁇ * phase to age, which significantly increases the ductility of the base material.
  • This aging heat treatment improves the weldability of the alloy, in particular at room temperature, compared to the untreated alloy.
  • the improved mechanical ductility of the alloy compared to the untreated alloy makes the component more directional (mechanically deformable) and / or better machinable or grinding.
  • the structure achieved in this way can have poorer properties compared to the structure before the heat treatment.
  • high-strength nickel super alloys such as IN939, Rene80 and IN738LC have been used in particular for large and thin-walled components such as Combustion chamber linings not used. These alloys have the ⁇ phase to increase strength and can now be processed and used with the method according to the invention without restrictions (with welds).
  • the material of choice was previously Hastelloy X. This material is easier to weld, but has limited high-temperature strength and directionality compared to the other material classes.
  • the component can, for example, be solution annealed (greater than or equal to 1180 ° C to, for example, 1200 ° C for the above-mentioned materials) with subsequent rapid cooling (for example, 20 ° - 40 ° C per minute to 800 ° C, then air cooling), that is faster than the cooling rate in the improvement heat treatment.
  • the outdated structure is "erased” again, ie the coarse precipitations at least partially disappear and the component regains its good high-temperature properties for the alloy, for example by adjusting a finely dispersed ⁇ ⁇ structure (rapid cooling).
  • the structure may have better properties for the area of application of the component than the structure that the component had after the heat treatment in order to improve the processability.
  • this ⁇ ⁇ phase is dissolved.
  • the ⁇ phase fails and coarsens accordingly.
  • the coarsening not only leads to an increase in the mean diameter of the ⁇ ⁇ phase, but also, for example, to spherodization of the ⁇ ⁇ phase, ie it is less cube-shaped and more platelet-shaped. Such coarsening leads to increased ductility.
  • a corresponding heat treatment is carried out which changes the microstructure in such a way that it improves the processability of the component, in particular at room temperature.
  • the process for improving the processability of the alloy can be used for newly manufactured components as well as for components that were in use (refurbishment).
  • the procedure is as follows, for example.
  • the used component is cleaned (removal of oxidation / corrosion products) and stripped, for example.
  • the component is then assessed, i.e. the detection of cracks and pores.
  • An aging heat treatment is then carried out, which is followed either by welding repair of the cracks and pores at room temperature or by straightening the component. Cold welding (hammering or hammering) of the welds produced in this way then takes place.
  • Solution annealing takes place, for example, at the same temperature as in the aging heat treatment, but with faster cooling, in order to avoid the coarsening of the ⁇ ⁇ structures. It cools down so quickly that the ⁇ 1 phase is not completely eliminated, but remains at least partially dissolved.
  • outsourcing can be carried out to remove the desired ⁇ ⁇ structure (fine blocky particles).
  • a type of filler metal or a filler metal with the same composition as the component is used in particular.
  • the same type means that it has approximately the same composition as the component or has the same high-temperature properties as the base material.
  • the components of the filler metal has the same proportions as the material of the component.
  • welding consumables can be dispensed with.
  • welding consumables that are less resistant to high temperatures should be avoided.
  • the filler metal can be hardened by precipitates, ie its strength can be increased, the weld point hardly or not at all reduces the strength of the component.
  • the filler metal should have at least a volume share of 35% (in the micrograph) for the precipitations (for example the ⁇ ⁇ phase).
  • the aging temperature of 1180 ° C for IN939 is deliberately chosen to be higher than that known from the prior art (1160 ° C, US Pat. No. 6,120,624).
  • the desired finely dispersed ⁇ phase is restored for the use of the component in order to achieve the required mechanical properties.
  • FIG. 3 shows different microstructures of a super alloy.
  • FIG. 3a shows the alloy with a cubic primary ⁇ ⁇ and a fine secondary ⁇ ⁇ phase, so that a high-strength alloy is obtained which has a low ductility.
  • FIG. 3b shows an outdated microstructure which has a platelet-shaped ⁇ phase, but no secondary ⁇ v phase. This microstructure has an increased ductility compared to FIG. 3a.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Arc Welding In General (AREA)
  • Heat Treatment Of Steel (AREA)

Abstract

Les alliages selon l'état antérieur de la technique présentent une aptitude à l'usinage qui n'est pas assez satisfaisante pour produire un composant. Selon la présente invention, un traitement thermique est effectué sur le composant dans une étape intermédiaire de procédé, afin d'améliorer son aptitude à l'usinage.
PCT/EP2003/013882 2002-12-10 2003-12-08 Procede pour produire un composant presentant une meilleure aptitude au soudage et/ou une meilleure aptitude a l'usinage mecanique a partir d'un alliage WO2004053181A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03782329A EP1570098A2 (fr) 2002-12-10 2003-12-08 Procede pour produire un composant presentant une meilleure aptitude au soudage et/ou une meilleure aptitude a l'usinage mecanique a partir d'un alliage
US10/538,414 US20060144477A1 (en) 2002-12-10 2003-12-08 Method for the production of a part having improved weldability and/or mechanical processability from an alloy
CN200380105754.3A CN1726297B (zh) 2002-12-10 2003-12-08 从合金制备有改善的可焊性和/或机械加工性的部件的方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP02027496.5 2002-12-10
EP02027496A EP1428897A1 (fr) 2002-12-10 2002-12-10 Méthode de fabrication d'un composant en alliage à soudabilité et/ou formabilité améliorée

Publications (2)

Publication Number Publication Date
WO2004053181A2 true WO2004053181A2 (fr) 2004-06-24
WO2004053181A3 WO2004053181A3 (fr) 2004-11-25

Family

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PCT/EP2003/013882 WO2004053181A2 (fr) 2002-12-10 2003-12-08 Procede pour produire un composant presentant une meilleure aptitude au soudage et/ou une meilleure aptitude a l'usinage mecanique a partir d'un alliage

Country Status (4)

Country Link
US (1) US20060144477A1 (fr)
EP (2) EP1428897A1 (fr)
CN (1) CN1726297B (fr)
WO (1) WO2004053181A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106048484A (zh) * 2016-07-06 2016-10-26 中南大学 一种采用两段阶梯应变速率工艺细化gh4169合金锻件晶粒组织的方法

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE502005005347D1 (de) 2005-10-24 2008-10-23 Siemens Ag Schweißzusatzwerkstoff, Verwendung des Schweißzusatzwerkstoffes und Verfahren zum Schweißen
EP1835040A1 (fr) 2006-03-17 2007-09-19 Siemens Aktiengesellschaft Matériau d'apport, utilisation du matériau d'apport et procédé de soudage d'une composante structurelle
EP2129486A1 (fr) * 2007-03-23 2009-12-09 Siemens Aktiengesellschaft Mélange de gaz protecteurs et procédé de soudage
EP2182084A1 (fr) 2008-11-04 2010-05-05 Siemens Aktiengesellschaft Matériau d'apport de soudure, utilisation du matériau d'apport de soudure et composant
US11515086B2 (en) * 2012-07-12 2022-11-29 Nissan Motor Co., Ltd. Method for manufacturing sintered magnet
US11072044B2 (en) * 2014-04-14 2021-07-27 Siemens Energy, Inc. Superalloy component braze repair with isostatic solution treatment

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US4574015A (en) * 1983-12-27 1986-03-04 United Technologies Corporation Nickle base superalloy articles and method for making
US4579602A (en) * 1983-12-27 1986-04-01 United Technologies Corporation Forging process for superalloys
FR2628349A1 (fr) * 1988-03-09 1989-09-15 Snecma Procede de forgeage de pieces en superalliage a base de nickel
EP0969114A2 (fr) * 1998-06-30 2000-01-05 Howmet Research Corporation Procédé de pré-soudage traitement thermique d'un superalliage à base de nickel

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US1531445A (en) * 1920-01-13 1925-03-31 Lake Simon Making metal castings
US2304976A (en) * 1939-09-07 1942-12-15 Budd Edward G Mfg Co Spot welded sheet material
US4222794A (en) * 1979-07-02 1980-09-16 United Technologies Corporation Single crystal nickel superalloy
JPS58107292A (ja) * 1981-12-21 1983-06-25 Kawasaki Heavy Ind Ltd 管の溶接継手部処理方法及び装置
CN1012182B (zh) * 1983-12-27 1991-03-27 联合工艺公司 镍基高温合金可锻性改进
US4769087A (en) * 1986-06-02 1988-09-06 United Technologies Corporation Nickel base superalloy articles and method for making
US5106010A (en) * 1990-09-28 1992-04-21 Chromalloy Gas Turbine Corporation Welding high-strength nickel base superalloys
US5071059A (en) * 1991-03-11 1991-12-10 General Motors Corporation Method for joining single crystal turbine blade halves
FR2712307B1 (fr) * 1993-11-10 1996-09-27 United Technologies Corp Articles en super-alliage à haute résistance mécanique et à la fissuration et leur procédé de fabrication.
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US5938863A (en) * 1996-12-17 1999-08-17 United Technologies Corporation Low cycle fatigue strength nickel base superalloys
US6648993B2 (en) * 2001-03-01 2003-11-18 Brush Wellman, Inc. Castings from alloys having large liquidius/solidus temperature differentials

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US4574015A (en) * 1983-12-27 1986-03-04 United Technologies Corporation Nickle base superalloy articles and method for making
US4579602A (en) * 1983-12-27 1986-04-01 United Technologies Corporation Forging process for superalloys
FR2628349A1 (fr) * 1988-03-09 1989-09-15 Snecma Procede de forgeage de pieces en superalliage a base de nickel
EP0969114A2 (fr) * 1998-06-30 2000-01-05 Howmet Research Corporation Procédé de pré-soudage traitement thermique d'un superalliage à base de nickel

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106048484A (zh) * 2016-07-06 2016-10-26 中南大学 一种采用两段阶梯应变速率工艺细化gh4169合金锻件晶粒组织的方法
CN106048484B (zh) * 2016-07-06 2018-02-23 中南大学 一种采用两段阶梯应变速率工艺细化gh4169合金锻件晶粒组织的方法

Also Published As

Publication number Publication date
WO2004053181A3 (fr) 2004-11-25
EP1570098A2 (fr) 2005-09-07
CN1726297A (zh) 2006-01-25
CN1726297B (zh) 2010-05-26
EP1428897A1 (fr) 2004-06-16
US20060144477A1 (en) 2006-07-06

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