GB2497128A - Nickel-based alloys comprising 0.2-0.6 % by weight silicon - Google Patents
Nickel-based alloys comprising 0.2-0.6 % by weight silicon Download PDFInfo
- Publication number
- GB2497128A GB2497128A GB1120731.3A GB201120731A GB2497128A GB 2497128 A GB2497128 A GB 2497128A GB 201120731 A GB201120731 A GB 201120731A GB 2497128 A GB2497128 A GB 2497128A
- Authority
- GB
- United Kingdom
- Prior art keywords
- text
- nickel
- alloy
- silicon
- hafnium
- 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- Withdrawn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
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 42
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 42
- 239000000956 alloy Substances 0.000 title claims abstract description 42
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 21
- 229910052710 silicon Inorganic materials 0.000 title claims abstract description 18
- 239000010703 silicon Substances 0.000 title claims abstract description 18
- 239000000203 mixture Substances 0.000 claims abstract description 15
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 12
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 12
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 11
- 239000011651 chromium Substances 0.000 claims abstract description 11
- 230000007797 corrosion Effects 0.000 claims abstract description 7
- 238000005260 corrosion Methods 0.000 claims abstract description 7
- 230000003647 oxidation Effects 0.000 claims abstract description 7
- 238000007254 oxidation reaction Methods 0.000 claims abstract description 7
- 230000001627 detrimental effect Effects 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract 10
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract 10
- 239000004411 aluminium Substances 0.000 claims abstract 10
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract 10
- 229910052782 aluminium Inorganic materials 0.000 claims abstract 10
- 229910052799 carbon Inorganic materials 0.000 claims abstract 10
- 239000012535 impurity Substances 0.000 claims abstract 10
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract 10
- 239000011733 molybdenum Substances 0.000 claims abstract 10
- 229910052715 tantalum Inorganic materials 0.000 claims abstract 10
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract 10
- 239000010936 titanium Substances 0.000 claims abstract 10
- 229910052719 titanium Inorganic materials 0.000 claims abstract 10
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract 9
- 229910052796 boron Inorganic materials 0.000 claims abstract 9
- 239000010941 cobalt Substances 0.000 claims abstract 9
- 229910017052 cobalt Inorganic materials 0.000 claims abstract 9
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract 9
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 3
- 239000005864 Sulphur Substances 0.000 claims description 3
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 2
- -1 boron O Chemical class 0.000 claims description 2
- BHEPBYXIRTUNPN-UHFFFAOYSA-N hydridophosphorus(.) (triplet) Chemical compound [PH] BHEPBYXIRTUNPN-UHFFFAOYSA-N 0.000 claims description 2
- 229910052749 magnesium Inorganic materials 0.000 claims description 2
- 239000011777 magnesium Substances 0.000 claims description 2
- 229910052726 zirconium Inorganic materials 0.000 claims description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims 9
- 238000012360 testing method Methods 0.000 description 5
- 238000005242 forging Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 229910001209 Low-carbon steel Inorganic materials 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009689 gas atomisation Methods 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 235000012771 pancakes Nutrition 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000002411 thermogravimetry Methods 0.000 description 1
- 229910001247 waspaloy Inorganic materials 0.000 description 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
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
Silicon the range 0.2-0.6 % by weight is included in nickel-based alloys to improve oxidation, hot corrosion and dwell crack growth resistance without a detrimental effect on thermal stability of the microstructure and properties. The alloy can have the following composition (by weight): 14.6-15.4 % chromium; 18-19 % cobalt; 4.75-5.25 % molybdenum; 2.8-3.2 % aluminium; 3.4-3.8 % titanium; 1.8-2.2 % tantalum; 0.4-0.6 % hafnium; 0.020-0.034 % carbon; 0.005-0.025 % boron; 0.2-0.6 % silicon, the balance being nickel and impurities. Another alloy has the following composition (by weight): 15 % chromium; 18.5 % cobalt; 5 % molybdenum; 3 % aluminium; 3.6 % titanium; 2 % tantalum; 0.5 % hafnium; 0.027 % carbon; 0.015 % boron; 0.2-0.6 % silicon, the balance being nickel and impurities. The alloy can be used to make gas turbine engine discs.
Description
A NICKEL-BASED ALLOY
This invention relates to nickel-based alloys, and particularly (although not exclusively) to nickel-based alloys suitable for use in discs of gas turbine engines.
Known nickel-based alloys were developed for applications such as blades, nozzle guide vanes and combustor components in gas turbine engines. For such applications, the alloys were designed to have improved oxidation resistance in the temperature range 760-1100 °C. Such alloys were typically wrought processed, to produce a polycrystall me microstructure, or investment cast, to produce conventionally cast, directionally solidified or single crystal microstructure.
The so-called third-generation powder metallurgy alloys, such as ME3, Alloy 10 and is LSHR, are nickel alloys developed for disc rotor applications at temperatures up to about 700 °C. They are all processed using powder metallurgy techniques.
To enable high-temperature strength and creep resistance to be optimised and to maintain a stable microstructure during exposure to high temperatures, the chromium content in these alloys is 11-15 wt%, compared with about 20 wt% in previous alloys such as Inconel® 718 and Waspaloy®. However, these alloy compositions are not optimised for certain other mechanical properties, such as oxidation resistance, resistance to hot corrosion damage and resistance to dwell crack growth. All of these properties are particularly important for rotor disc applications, because they can limit component life.
The inventors have discovered a modification to the composition of the known nickel-based alloy RR1 000 that improves oxidation, hot corrosion and dwell crack growth resistance, without the detrimental effects on the thermal stability of the microstructure and on other material properties that have been found with known alloys.
Accordingly, the invention provides a nickel-based alloy and a component made from such an alloy, as set out in the claims.
Embodiments of the invention will now be described, by way of example only, so that it can be better understood how it is to be put into effect.
The inventors have discovered the unexpected result that adding silicon, in a defined range of weight percentage, to the composition of the known nickel-based alloy RR1 000 improves oxidation, hot corrosion and dwell crack growth resistance without the detrimental effects on the thermal stability of the microstructure and on other material properties that have been found with known alloys.
Powder particles of the compositions shown in Table 1 were produced by argon gas atomisation. The particles were screened to a final screen size of 53 pm and filled into a mild steel container. Hot isostatic pressing was then used to consolidate the particles.
The resulting compacts were isothermally forged to produce pancake forgings, and solution heat treated to produce fine-grained (average grain size <10 pm) and coarse-grained (average grain size 20-65 pm) microstructures.
Table 1
Alloy Cr Co Mo Al Ti Ta Hf C B Zr Si Ni RR1000 15 18.5 5 3 3.6 2 0.5 0.027 0.015 0.06 0 rem.
#1 15 18.5 5 3 3.6 2 0.5 0.027 0.015 0.06 0.2 rem.
#2 15 18.5 5 3 3.6 2 0.5 0.027 0.015 0.06 0.5 rem.
Oxidation damage at temperatures between 700 and 800 °C was evaluated by weight change by thermogravimetric analysis on RR1000 and on the alloys #1 and #2 according to the invention. The test pieces were prepared from forgings having fine-and coarse-grained microstructures.
Hot corrosion resistance was evaluated by deposit recoat experiments at 700 °C on the three alloys. The test pieces were prepared from forgings having a fine-grained microstructure. In these tests, samples were coated with deposits of 98% Na2SO4I 2% NaCI in a gas stream of air containing 300 vpm SO2. Corrosion damage is quantified by dimensional metrology of the samples before and after exposure, to determine the amount of sound metal loss.
Dwell crack growth resistance was evaluated in laboratory air at 700 °C on 5mm x 5mm square section, corner notch test pieces. The test pieces were prepared from forgings having a coarse-grained microstructure. Fatigue cycles consisting of a 3600s dwell period at peak load and a stress ratio of 0.1 were used.
By adding a quantity of silicon between 0.2 and 0.6 wt% to the known RR1 000 alloy composition, an unexpected improvement in key material properties has been achieved in temperature ranges that are important for gas turbine rotor disc applications, without the detrimental effects in other properties previously associated with such improvements.
Further improvements may be achievable with higher levels of silicon, but these are considered to reduce the stability of the microstructure, and promote the precipitation of topological close-packed phases (e.g. sigma) during prolonged exposure to temperatures above about 675 °C. Such phases form at grain boundaries and are detrimental to tensile strength and ductility, stress rupture and dwell crack growth resistance.
It is believed that additions of silicon, as described above, could provide similarly beneficial results in other rotor disc alloys. The results are not dependent on a particular processing method, but can be realised for cast, wrought and powder processed alloys.
It is believed that the most significant benefits are achieved when silicon is used in combination with reactive elements such as hafnium, zirconium and magnesium that "get" oxygen and sulphur and low levels of sulphur and phosphorous.
Claims (5)
- <claim-text>CLAIMS1. A nickel-based alloy including between 0.2 wt% and 0.6 wt% silicon to improve oxidation resistance, dwell crack growth resistance and hot corrosion resistance without detrimental effect on other mechanical properties of the alloy.</claim-text> <claim-text>2. An alloy as claimed in claim 1, further including at least one of the following: hafnium <= 0.75 wt%; zirconium <= 0.1 wt%; magnesium <= 0O3wt%; sulphur c= 5 ppm; phosphorous C 10 ppm.</claim-text> <claim-text>3. An alloy as claimed in claim 1 having the following composition in weight percent: chromium 14.6-15.4%; cobalt 18-19%; molybdenum 4.75-5.25%; aluminium 2.8-3.2%; titanium 3.4-3.8%; tantalum 1.8-2.2%; hafnium 0.4-0.6%; carbon 0.020-0.034%; boron 0.005-0.025%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities.</claim-text> <claim-text>4. An alloy as claimed in claim 1, having the following composition in weight percent: chromium 15%; cobalt 18.5%; molybdenum 5%; aluminium 3%; titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.01 5%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities.</claim-text> <claim-text>5. An alloy as claimed in claim 1, having the following composition in weight percent: chromium 15%; cobalt 18.5%; molybdenum 5%; aluminium 3%; titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.01 5%; silicon 0.2%; the remainder being nickel and incidental impurities.</claim-text> <claim-text>6. An alloy as claimed in claim 1, having the following composition in weight percent: chromium 15%; cobalt 18.5%; molybdenum 5%; aluminium 3%; titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.015%; silicon 0.5%; the remainder being nickel and incidental impurities.</claim-text> <claim-text>7. A component formed of an alloy as claimed in any preceding claim.</claim-text> <claim-text>8. A component as claimed in claim 7, the component being a disc for a gas turbine engine.</claim-text> <claim-text>9. An alloy substantially as described in this specification.</claim-text> <claim-text>10. A component formed of an alloy substantially as described in this specification.Amendments to the claims have been made as follows:CLAIMS1. A nickel-based alloy having the following composition in weight percent: chromium 14.6-15.4%; cobalt 18-19%; molybdenum 4.75-5.25%; aluminium 2.8-3.2%; titanium 3.4-3.8%; tantalum 1.8-2.2%; hafnium 0.4-0.6%; carbon 0.020-0.034%; boron O.005-0.025%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities.
- 2. An alloy as claimed in claim 1, having the following composition in weight (0 percent: 04 chromium 15%; cobalt 18.5%; molybdenum 5%; aluminium 3%; titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.01 5%; silicon 0.2-0.6%; the remainder being nickel and incidental impurities.
- 3. An alloy as claimed in claim 1, having the following composition in weight percent: chromium 15%;Scobalt 18.5%; molybdenum 5%; aluminium 3%; titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.01 5%; silicon 0.2%; the remainder being nickel and incidental impurities.
- 4. An alloy as claimed in claim 1, having the following composition in weight percent: chromium 15%; cobalt 18.5%; molybdenum 5%; aluminium 3%; 04 titanium 3.6%; tantalum 2%; hafnium 0.5%; carbon 0.027%; boron 0.015%; silicon 0.5%; the remainder being nickel and incidental impurities.
- 5. A nickel-based alloy substantially as described in this specification.</claim-text>
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1120731.3A GB2497128A (en) | 2011-12-02 | 2011-12-02 | Nickel-based alloys comprising 0.2-0.6 % by weight silicon |
| US13/686,220 US20130142661A1 (en) | 2011-12-02 | 2012-11-27 | Nickel-based alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1120731.3A GB2497128A (en) | 2011-12-02 | 2011-12-02 | Nickel-based alloys comprising 0.2-0.6 % by weight silicon |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201120731D0 GB201120731D0 (en) | 2012-01-11 |
| GB2497128A true GB2497128A (en) | 2013-06-05 |
Family
ID=45509049
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1120731.3A Withdrawn GB2497128A (en) | 2011-12-02 | 2011-12-02 | Nickel-based alloys comprising 0.2-0.6 % by weight silicon |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US20130142661A1 (en) |
| GB (1) | GB2497128A (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10935241B2 (en) * | 2014-05-09 | 2021-03-02 | Raytheon Technologies Corporation | Additively manufactured hotspot portion of a turbine engine component having heat resistant properties and method of manufacture |
| CN106563929B (en) * | 2015-10-08 | 2019-09-17 | 利宝地工程有限公司 | Repair and manufacture the method and turbine engine components of turbine engine components |
| US10415121B2 (en) | 2016-08-05 | 2019-09-17 | Onesubsea Ip Uk Limited | Nickel alloy compositions for aggressive environments |
| CN113186431A (en) * | 2021-05-06 | 2021-07-30 | 哈尔滨工业大学（深圳） | Nickel-based high-temperature alloy powder suitable for powder metallurgy and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB607616A (en) * | 1945-11-28 | 1948-09-02 | Harold Ernest Gresham | Nickel base alloy |
| GB708820A (en) * | 1951-03-29 | 1954-05-12 | Carpenter Steel Co | Improvements in alloys |
| GB943141A (en) * | 1961-01-24 | 1963-11-27 | Rolls Royce | Method of heat treating nickel alloys |
| US3420660A (en) * | 1963-09-20 | 1969-01-07 | Nippon Yakin Kogyo Co Ltd | High strength precipitation hardening heat resisting alloys |
| GB1512984A (en) * | 1974-06-17 | 1978-06-01 | Cabot Corp | Oxidation resistant nickel alloys and method of making the same |
| US20020195175A1 (en) * | 2001-06-04 | 2002-12-26 | Kiyohito Ishida | Free-cutting Ni-base heat-resistant alloy |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1212020A (en) * | 1981-09-14 | 1986-09-30 | David N. Duhl | Minor element additions to single crystals for improved oxidation resistance |
| US6468368B1 (en) * | 2000-03-20 | 2002-10-22 | Honeywell International, Inc. | High strength powder metallurgy nickel base alloy |
| GB0719195D0 (en) * | 2007-10-02 | 2007-11-14 | Rolls Royce Plc | A nickel base superalloy |
-
2011
- 2011-12-02 GB GB1120731.3A patent/GB2497128A/en not_active Withdrawn
-
2012
- 2012-11-27 US US13/686,220 patent/US20130142661A1/en not_active Abandoned
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB607616A (en) * | 1945-11-28 | 1948-09-02 | Harold Ernest Gresham | Nickel base alloy |
| GB708820A (en) * | 1951-03-29 | 1954-05-12 | Carpenter Steel Co | Improvements in alloys |
| GB943141A (en) * | 1961-01-24 | 1963-11-27 | Rolls Royce | Method of heat treating nickel alloys |
| US3420660A (en) * | 1963-09-20 | 1969-01-07 | Nippon Yakin Kogyo Co Ltd | High strength precipitation hardening heat resisting alloys |
| GB1512984A (en) * | 1974-06-17 | 1978-06-01 | Cabot Corp | Oxidation resistant nickel alloys and method of making the same |
| US20020195175A1 (en) * | 2001-06-04 | 2002-12-26 | Kiyohito Ishida | Free-cutting Ni-base heat-resistant alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201120731D0 (en) | 2012-01-11 |
| US20130142661A1 (en) | 2013-06-06 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |