EP1570098A2 - 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 alliageInfo
- Publication number
- EP1570098A2 EP1570098A2 EP03782329A EP03782329A EP1570098A2 EP 1570098 A2 EP1570098 A2 EP 1570098A2 EP 03782329 A EP03782329 A EP 03782329A EP 03782329 A EP03782329 A EP 03782329A EP 1570098 A2 EP1570098 A2 EP 1570098A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat treatment
- component
- welding
- alloy
- carried out
- 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.)
- Withdrawn
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 37
- 239000000956 alloy Substances 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 36
- 238000004519 manufacturing process Methods 0.000 title claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 51
- 238000003466 welding Methods 0.000 claims description 30
- 238000001816 cooling Methods 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 13
- 239000000945 filler Substances 0.000 claims description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 239000002244 precipitate Substances 0.000 claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 7
- 238000001513 hot isostatic pressing Methods 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 238000001556 precipitation Methods 0.000 claims description 6
- 238000000137 annealing Methods 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 5
- 238000005056 compaction Methods 0.000 claims description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 239000000155 melt Substances 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- 238000010583 slow cooling Methods 0.000 claims description 3
- 239000010941 cobalt Substances 0.000 claims description 2
- 229910017052 cobalt Inorganic materials 0.000 claims description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 2
- 229910052742 iron Inorganic materials 0.000 claims description 2
- 238000007669 thermal treatment Methods 0.000 abstract 1
- 230000032683 aging Effects 0.000 description 18
- 238000007906 compression Methods 0.000 description 5
- 239000011148 porous material Substances 0.000 description 4
- 238000000227 grinding Methods 0.000 description 3
- 238000005336 cracking Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000008021 deposition Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 238000005245 sintering Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000029142 excretion Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 238000001000 micrograph Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000012946 outsourcing Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000009419 refurbishment Methods 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 238000005493 welding type Methods 0.000 description 1
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)
- Pressure Welding/Diffusion-Bonding (AREA)
- Powder Metallurgy (AREA)
- Arc Welding In General (AREA)
- Heat Treatment Of Steel (AREA)
Abstract
Priority Applications (1)
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 |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02027496 | 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 |
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 |
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 |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1570098A2 true EP1570098A2 (fr) | 2005-09-07 |
Family
ID=32319566
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02027496A Withdrawn EP1428897A1 (fr) | 2002-12-10 | 2002-12-10 | Méthode de fabrication d'un composant en alliage à soudabilité et/ou formabilité améliorée |
EP03782329A Withdrawn 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 |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02027496A Withdrawn EP1428897A1 (fr) | 2002-12-10 | 2002-12-10 | Méthode de fabrication d'un composant en alliage à soudabilité et/ou formabilité améliorée |
Country Status (4)
Country | Link |
---|---|
US (1) | US20060144477A1 (fr) |
EP (2) | EP1428897A1 (fr) |
CN (1) | CN1726297B (fr) |
WO (1) | WO2004053181A2 (fr) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1777312B1 (fr) | 2005-10-24 | 2008-09-10 | Siemens Aktiengesellschaft | Matériau d'apport pour soudage, utilisation du matériau d'apport pour soudage et procédé de soudage |
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 |
WO2008116478A1 (fr) * | 2007-03-23 | 2008-10-02 | 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 |
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 |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US4574015A (en) * | 1983-12-27 | 1986-03-04 | United Technologies Corporation | Nickle base superalloy articles and method for making |
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 |
US4579602A (en) * | 1983-12-27 | 1986-04-01 | United Technologies Corporation | Forging process for superalloys |
US4769087A (en) * | 1986-06-02 | 1988-09-06 | United Technologies Corporation | Nickel base superalloy articles and method for making |
FR2628349A1 (fr) * | 1988-03-09 | 1989-09-15 | Snecma | Procede de forgeage de pieces en superalliage a base de nickel |
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. |
DE19624056A1 (de) * | 1996-06-17 | 1997-12-18 | Abb Research Ltd | Nickel-Basis-Superlegierung |
US5938863A (en) * | 1996-12-17 | 1999-08-17 | United Technologies Corporation | Low cycle fatigue strength nickel base superalloys |
US6120624A (en) * | 1998-06-30 | 2000-09-19 | Howmet Research Corporation | Nickel base superalloy preweld heat treatment |
US6648993B2 (en) * | 2001-03-01 | 2003-11-18 | Brush Wellman, Inc. | Castings from alloys having large liquidius/solidus temperature differentials |
-
2002
- 2002-12-10 EP EP02027496A patent/EP1428897A1/fr not_active Withdrawn
-
2003
- 2003-12-08 US US10/538,414 patent/US20060144477A1/en not_active Abandoned
- 2003-12-08 CN CN200380105754.3A patent/CN1726297B/zh not_active Expired - Fee Related
- 2003-12-08 WO PCT/EP2003/013882 patent/WO2004053181A2/fr not_active Application Discontinuation
- 2003-12-08 EP EP03782329A patent/EP1570098A2/fr not_active Withdrawn
Non-Patent Citations (1)
Title |
---|
See references of WO2004053181A3 * |
Also Published As
Publication number | Publication date |
---|---|
US20060144477A1 (en) | 2006-07-06 |
EP1428897A1 (fr) | 2004-06-16 |
WO2004053181A2 (fr) | 2004-06-24 |
WO2004053181A3 (fr) | 2004-11-25 |
CN1726297B (zh) | 2010-05-26 |
CN1726297A (zh) | 2006-01-25 |
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Inventor name: GOLDSCHMIDT, DIRK Inventor name: COX, NIGEL-PHILIP Inventor name: YUSHCHENKO, KONSTANTIN, A. Inventor name: WILKENHOENER, ROLF |
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