CA2503326A1 - Heat treatment of alloys having elements for improving grain boundary strength - Google Patents
Heat treatment of alloys having elements for improving grain boundary strength Download PDFInfo
- Publication number
- CA2503326A1 CA2503326A1 CA002503326A CA2503326A CA2503326A1 CA 2503326 A1 CA2503326 A1 CA 2503326A1 CA 002503326 A CA002503326 A CA 002503326A CA 2503326 A CA2503326 A CA 2503326A CA 2503326 A1 CA2503326 A1 CA 2503326A1
- Authority
- CA
- Canada
- Prior art keywords
- heat treatment
- alloy
- casting
- chosen
- degrees
- 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
Links
- 238000010438 heat treatment Methods 0.000 title claims abstract 28
- 229910045601 alloy Inorganic materials 0.000 title claims abstract 16
- 239000000956 alloy Substances 0.000 title claims abstract 16
- 238000005266 casting Methods 0.000 claims abstract 13
- 229910052796 boron Inorganic materials 0.000 claims abstract 7
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract 4
- 229910000601 superalloy Inorganic materials 0.000 claims abstract 2
- 238000000034 method Methods 0.000 claims 28
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims 11
- 230000035882 stress Effects 0.000 claims 8
- 229910052759 nickel Inorganic materials 0.000 claims 5
- 239000013078 crystal Substances 0.000 claims 4
- 229910052799 carbon Inorganic materials 0.000 claims 3
- 229910052804 chromium Inorganic materials 0.000 claims 3
- 229910052750 molybdenum Inorganic materials 0.000 claims 3
- 229910052715 tantalum Inorganic materials 0.000 claims 3
- 229910052721 tungsten Inorganic materials 0.000 claims 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims 1
- 230000032683 aging Effects 0.000 claims 1
- 229910017052 cobalt Inorganic materials 0.000 claims 1
- 239000010941 cobalt Substances 0.000 claims 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims 1
- 229910052735 hafnium Inorganic materials 0.000 claims 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims 1
- 239000011159 matrix material Substances 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 229910052758 niobium Inorganic materials 0.000 claims 1
- 229910052710 silicon Inorganic materials 0.000 claims 1
- 229910052845 zircon Inorganic materials 0.000 claims 1
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 claims 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to heat treatment of cast alloys, such as superalloys, which have at least one addition, so as to improve grain boundary strength. Typically after casting, components often reveal low or no transverse grain boundary strength so that cracks can appear and decrease the yield rate.
The invention relates to providing improved grain boundary strength to significantly improve transverse stress rupture strength and ductility of directionally solidified columnar grain castings. The heat treatment involves at least one addition, such as boron, to improve the grain boundary strength.
The invention relates to providing improved grain boundary strength to significantly improve transverse stress rupture strength and ductility of directionally solidified columnar grain castings. The heat treatment involves at least one addition, such as boron, to improve the grain boundary strength.
Claims (22)
1. A method of heat treating cast alloys having at least one addition, which improves the grain boundary strength, wherein the alloy has a secondary phase after the casting, which can be solved in the matrix of the alloy at a solution temperature, wherein the heat treatment is performed in such a way, that the secondary phase is only partly solved.
2. A method of claim 1, wherein at least one ageing treatment is performed after the heat treatment.
3. A method of claim 1, wherein the temperature of the heat treatment is smaller than the fully solution temperature.
4. A method of claim 1 or 3, wherein the duration of the heat treatment is chosen in such a way, that the secondary is not completely solved.
5. A method of claim 1, wherein the heat treatment is performed with nickel or cobalt based superalloys.
6. A method of claim 1, wherein the heat treatment is performed with hollow components.
1. A method of claim 6, wherein the heat treatment is performed with components having a length of at least 200mm.
2. A method of claim 6, wherein the heat treatment is performed with hollow components having a thickness of an outer wall smaller than 8mm.
3. A method of claim 5, wherein the~secondary phase is the .gamma.'-phase.
4. A method of claim 1, wherein the heat treatment is performed with an alloy having boron as an addition.
5. A method of claim 1, wherein the heat treatment is performed with an alloy having carbon as an addition.
6. A method of claim 1, wherein the heat treatment is performed with an alloy having a directionally solidified columnar grains.
1. A method of claim 6, wherein the heat treatment is performed with components having a length of at least 200mm.
2. A method of claim 6, wherein the heat treatment is performed with hollow components having a thickness of an outer wall smaller than 8mm.
3. A method of claim 5, wherein the~secondary phase is the .gamma.'-phase.
4. A method of claim 1, wherein the heat treatment is performed with an alloy having boron as an addition.
5. A method of claim 1, wherein the heat treatment is performed with an alloy having carbon as an addition.
6. A method of claim 1, wherein the heat treatment is performed with an alloy having a directionally solidified columnar grains.
7. A method of claim 1, wherein the heat treatment is performed with an alloy having a single crystal structure.
8. A method of claim 1, wherein the parameters of the heat treatment is chosen in such a way that the amount of the secondary phase brought into solution is smaller than 90vol%.
9. A method of claim 1, wherein the parameters of the heat treatment is chosen in such a way that the amount of the secondary phase brought into solution is smaller than 70vol%.
10.A method of claim 1, wherein the parameters of the heat treatment is chosen in such a way that the amount of the secondary phase brought into solution is smaller than 50vol%.
11.A method of claim 1, wherein the parameters of the heat treatment is chosen in such a way that the amount of the secondary phase brought into solution is smaller than 30vol%.
12.A method of claim 1, wherein the heat treatment is performed with a directionally solidified columnar grain nickel base alloy casting, consisting essentially of, in weight % of about 9.5% to 14% Cr, about 7% to 11% Co, about 1% to 2.5% Mo, about 3% to 6% W, about 1% to 6% Ta, about 3% to 4% Al, about 3% to 5% Ti ,
13 about 0% to 1% Nb, and balance essentially Ni and B present in an amount effective to substantially improve transverse stress rupture strength of said casting as compared to a similar casting without boron present.
13.A method of claim 18, wherein the heat treatment is performed with an alloy, wherein B is present in the range of about 0.0030 to about 0.018% by weight.
13.A method of claim 18, wherein the heat treatment is performed with an alloy, wherein B is present in the range of about 0.0030 to about 0.018% by weight.
14.A method of claim 18, wherein the alloy after the heat treatment has a stress rupture life of at least about 100 hours and elongation to fracture of at least about 2.5% when tested at a temperature of 750 degrees C (1382 degrees F) and stress of 660 MPa (95.7 Ksi) applied in a direction perpendicular to a <001> crystal axis of said casting.
15.A method of claim 1, wherein the heat treatment is performed with a directionally solidified columnar grain nickel base alloy casting consisting essentially of, in weight %, of about 11.6% to 12.70% Cr, about 8.5% to 9.5% Co, about 1.65% to 2.15% Mo, about 3.5% to 4.10% W, about 4.8% to 5.20% Ta, about 3.4% to 3.80% Al, about 3.9% to 4.25% Ti, about 0.05% to 0.11% C, about 0.003% to 0.0175% B, balance essentially Ni and having substantially improved transverse stress rupture strength as compared to a similar casting without boron present.
16.A method of claim 21, wherein the alloy after the heat treatment has a stress rupture life of at least about 120 hours and elongation of at least about 2.5% when tested at a temperature of 750 degrees C (1382 degrees F) and stress of 660 MPa (95.7 Ksi) applied perpendicular to a <001> crystal axis of said casting.
17.A method of claim 1, wherein the heat treatment is performed with directionally solidified columnar grain nickel base alloy casting having a nominal composition consisting essentially of, in weight %, of about 12.00% Cr, about 9.00% Co, about 1.85% Mo, about 3.70% W, about 5.10% Ta, about 3.60% Al, about 4.00% Ti, about 0.0125% B, about 0.09% C, balance essentially Ni and having a stress rupture life of at least about 100 hours and elongation to fracture of at least about 2.5% when tested at a temperature of 750 degrees C (1382 degrees F) and stress of 660 MPa (95.7 Ksi) applied perpendicular to a <001> crystal axis of said casting.
18.A Method of claim 1, wherein the heat treatment is performed after casting.
19.A Method of claim 4, wherein the fully solution temperature is used.
20.A Method of claim 6, wherein the hollow components are chosen of the group consisting of vanes, blades and liners.
21.Method of claim 1, wherein the heat treatment is performed with massive components.
22.A method of claim 1, wherein the heat treatment is performed with an alloy having an addition selected from the group consisting of Zircon, Silizium, Hafnium.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/EP2002/011856 WO2004038056A1 (en) | 2002-10-23 | 2002-10-23 | Heat treatment of alloys having elements for improving grain boundary strength |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2503326A1 true CA2503326A1 (en) | 2004-05-06 |
| CA2503326C CA2503326C (en) | 2011-02-08 |
Family
ID=32116204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2503326A Expired - Fee Related CA2503326C (en) | 2002-10-23 | 2002-10-23 | Heat treatment of alloys having elements for improving grain boundary strength |
Country Status (8)
| Country | Link |
|---|---|
| EP (1) | EP1438441B1 (en) |
| JP (1) | JP4812301B2 (en) |
| CN (1) | CN100449031C (en) |
| AU (1) | AU2002337170A1 (en) |
| CA (1) | CA2503326C (en) |
| DE (1) | DE60215035T2 (en) |
| ES (1) | ES2276959T3 (en) |
| WO (1) | WO2004038056A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1849879A1 (en) * | 2006-04-26 | 2007-10-31 | Siemens Aktiengesellschaft | Cyclic heat treatment process for a superalloy |
| EP1900839B1 (en) * | 2006-09-07 | 2013-11-06 | Alstom Technology Ltd | Method for the heat treatment of nickel-based superalloys |
| WO2011047714A1 (en) * | 2009-10-20 | 2011-04-28 | Siemens Aktiengesellschaft | Alloy for directional solidification and component made of stem-shaped crystals |
| EP2769802A1 (en) | 2013-02-22 | 2014-08-27 | Siemens Aktiengesellschaft | Improved welding material with regard to weldability and grain stabilisation, method and component |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999067435A1 (en) * | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
-
2002
- 2002-10-23 JP JP2004545738A patent/JP4812301B2/en not_active Expired - Fee Related
- 2002-10-23 WO PCT/EP2002/011856 patent/WO2004038056A1/en active IP Right Grant
- 2002-10-23 CA CA2503326A patent/CA2503326C/en not_active Expired - Fee Related
- 2002-10-23 AU AU2002337170A patent/AU2002337170A1/en not_active Abandoned
- 2002-10-23 ES ES02772392T patent/ES2276959T3/en not_active Expired - Lifetime
- 2002-10-23 CN CNB028277384A patent/CN100449031C/en not_active Expired - Fee Related
- 2002-10-23 EP EP02772392A patent/EP1438441B1/en not_active Expired - Lifetime
- 2002-10-23 DE DE60215035T patent/DE60215035T2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| AU2002337170A1 (en) | 2004-05-13 |
| EP1438441A1 (en) | 2004-07-21 |
| JP4812301B2 (en) | 2011-11-09 |
| DE60215035D1 (en) | 2006-11-09 |
| EP1438441B1 (en) | 2006-09-27 |
| CN1617944A (en) | 2005-05-18 |
| JP2006503980A (en) | 2006-02-02 |
| ES2276959T3 (en) | 2007-07-01 |
| CN100449031C (en) | 2009-01-07 |
| WO2004038056A1 (en) | 2004-05-06 |
| AU2002337170A8 (en) | 2004-05-13 |
| CA2503326C (en) | 2011-02-08 |
| DE60215035T2 (en) | 2007-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US12024758B2 (en) | Nickel-based superalloy and parts made from said superalloy | |
| JP4995570B2 (en) | Nickel base alloy and heat treatment method of nickel base alloy | |
| EP1930455B1 (en) | Nickel-base superalloy with excellent unsusceptibility to oxidation | |
| KR101232533B1 (en) | Cobalt-chromium-iron-nickel-alloys amenable to nitrides strengthening | |
| EP3183372B1 (en) | Enhanced superalloys by zirconium addition | |
| EP2778241B1 (en) | Heat-resistant nickel-based superalloy | |
| US20040011439A1 (en) | Directionally solidified casting with improved transverse stress rupture strength | |
| US20020062886A1 (en) | Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof | |
| US20130206287A1 (en) | Co-based alloy | |
| US20070199628A1 (en) | Nickel-Base Superalloy | |
| EP2420584A1 (en) | Nickel-base single-crystal superalloy and turbine wing using same | |
| JP2007162041A (en) | High strength and high ductility Ni-base superalloy, member using the same, and manufacturing method | |
| JP3559670B2 (en) | High-strength Ni-base superalloy for directional solidification | |
| CA2503326A1 (en) | Heat treatment of alloys having elements for improving grain boundary strength | |
| US20050000603A1 (en) | Nickel base superalloy and single crystal castings | |
| JP4607490B2 (en) | Nickel-base superalloy and single crystal casting | |
| JP4184648B2 (en) | Ni-based single crystal alloy excellent in strength and corrosion resistance and its manufacturing method | |
| US20120175027A1 (en) | Heat Treatment of Alloys Having Elements for Improving Grain Boundary Strength | |
| EP3428297B1 (en) | Ni-BASED UNIDIRECTIONALLY SOLIDIFIED ALLOY | |
| US20060249233A1 (en) | Heat treatment of alloys having elements for improving grain boundary strength | |
| US20080163962A1 (en) | Directionally solidified casting with improved transverse stress rupture strength | |
| GB2403225A (en) | A nickel based superalloy | |
| JP2000328162A (en) | Nickel base single crystal heat resistant superalloy, its production and turbine blade using nickel base single crystal heat resistant superalloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20141023 |