GB2112812A - High strength corrosion resistant nickel base single crystal article - Google Patents
High strength corrosion resistant nickel base single crystal article Download PDFInfo
- Publication number
- GB2112812A GB2112812A GB08236691A GB8236691A GB2112812A GB 2112812 A GB2112812 A GB 2112812A GB 08236691 A GB08236691 A GB 08236691A GB 8236691 A GB8236691 A GB 8236691A GB 2112812 A GB2112812 A GB 2112812A
- Authority
- GB
- United Kingdom
- Prior art keywords
- hrs
- single crystal
- high strength
- nickel base
- corrosion resistant
- 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
- 239000013078 crystal Substances 0.000 title claims abstract description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims description 16
- 229910052759 nickel Inorganic materials 0.000 title claims description 8
- 230000007797 corrosion Effects 0.000 title description 6
- 238000005260 corrosion Methods 0.000 title description 6
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 25
- 239000000956 alloy Substances 0.000 claims abstract description 25
- 229910000601 superalloy Inorganic materials 0.000 claims description 7
- 229910052750 molybdenum Inorganic materials 0.000 claims description 2
- 229910052758 niobium Inorganic materials 0.000 claims description 2
- 229910052715 tantalum Inorganic materials 0.000 claims description 2
- 230000001747 exhibiting effect Effects 0.000 claims 1
- 229910052721 tungsten Inorganic materials 0.000 claims 1
- 239000000203 mixture Substances 0.000 abstract description 9
- 238000010438 heat treatment Methods 0.000 description 8
- 230000008901 benefit Effects 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 2
- 229910052796 boron Inorganic materials 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 229910052735 hafnium Inorganic materials 0.000 description 2
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000011282 treatment Methods 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
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Mechanical Engineering (AREA)
- Inorganic Chemistry (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
- Powder Metallurgy (AREA)
- Adornments (AREA)
- Chemically Coating (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The article is formed of an alloy containing in wt % <IMAGE> Such single crystals, display elevated temperature rupture lives which are least 10x of that displayed by conventionally cast alloys of similar compositions.
Description
SPECIFICATION
High Strength corrosion resistant nickel base single crystal article
This invention relates to the field of high strength nickel base superalloy articles such as gas turbine components which are both resistant to corrosion and are capable of operating at high temperatures. This invention also relates to the field of single crystal superalloy articles.
Increasing demands for efficiency in gas turbine engines have resulted in demands for materials capable of withstanding more severe operating conditions. In particular, increased temperature capabilities are required for certain applications along with resistance to corrosion.
U.S. patent 3 494 709 describes the fabrication of gas turbine components in single crystal form for improved performance. U.S. patent 4 11 6 723 describes a heat treatment applicable to single crystal superalloy articles for the purpose of enhanced properties. U.S. patent 3 619 182 assigned to
International Nickel Corporation, describes a moderate strength superalloy having superior corrosion resistance.
According to the present invention alloys in the composition range 9.514% Cr, 7-11% Co, 12.5% Mo, 3-6% w, 3-6% Ta, 3% Al, 3-5% Ti, 0--1% Nb balance essentially nickel are provided with improved mechanical properties through fabrication of the alloy in single crystal form.
The resultant single crystal article is then preferably heat treated. Heat treated single crystal alloys of this composition display at least a lOX improvement in rupture life in comparison to alloys of similar composition which have been conventionally solidified to produce an equiaxed polycrystalline structure.
Other features and advantages will be apparent from the specification and claims which illustrate an embodiment of the invention.
This invention had its origin in a surprising and unexpected observation. A series of commercial superalloys were evaluated in three different forms. Samples were prepared in polycrystalline (conventionally cast) form, columnar grain (directionally solidified) form, and single crystal (directionally solidified) form. The alloys tested were MAR-M200, MAR-M247, IN 939 and IN 792. The first two alloys are proprietary alloys produced under license from the Martin Metals Corporation and the latter two alloys are proprietary alloys supplied by the International Nickel Corporation. The composition of these alloys as tested is given in Table 1. Through reference to Table 1 it can be seen that the conventionally cast materials contained the grain boundary strengtheners carbon, boron, and zirconium as did all the columnar grain materials.Most of the columnar grained samples also contained additions of hafnium for improved transverse ductility. Most of the single crystal samples did not contain any of the elements carbon, boron, zirconium or hafnium.
The cast alloy samples were heat treated as described in Table 2 and the heat treatment described therein are conventional heat treatments which are typical of those which would likely be selected by one skilled in the art.
These alloy samples were creep tested under different conditions of load and temperature with the results shown in Table 3. Table 3 shows the surprising and unexpected benefits which derive from the fabrication of the modified IN 792 alloy in single crystal form. For the MAR-M200, MAR-M247 and
IN 939 alloys the ratio of rupture life of the single crystal samples to the conventional cast samples averaged 4.1 X, however for the case of the IN 792, the ratio of single crystal rupture life to conventionally cast rupture life was more than 1 7 X (average of 8700C/344.75 MPa and 9800C/186.16 MPa tests). This degree of improvement is surprising and unexpected.It thus appears that the improvement (in creep rupture life) obtained by fabricating (modified) IN 792 in single crystal form is about 370% greater than the benefit one would predict based on the evidence of other superalloys. For purposes of defining the invention results, it appears that a minimum 10 X improvement in creep rupture life will be obtained.
A similar conclusion is reached when one considers the time to 1% creep. In this case, based on the two MAR M alloys, one would expect an average improvement of 5.4 X by changing the test sample macrostructure from polycrystalline to single crystal (in concert with minor composition and heat treatment changes). In fact, making this change to the modified IN 792 alloy results in an average benefit of about 1 2.6 X. Again, this is a disproportionate and unexpected improvement and not predictable from the prior knowledge in the art.
The substantial improvement in creep properties is rendered more significant because the invention composition is slightly less dense than the other alloys evaluated. Further, the notable resistance to corrosion exhibited by alloy IN 792 is fully maintained in this invention.
A heat treatment as described in U.S. 4 11 6 723 is preferred in order to obtain the maximum increase in properties. Such a heat treatment involves solutioning of the gamma prime phase and homogenization of the cast structure at a temperature above the gamma prime solvus 1 2320C for the invention composition) followed by one or more aging treatments at a lower temperature. U.S. patent 4 11 6 723 is incorporated herein by reference.
It should be understood that the invention is not limited to the particular embodiments shown and described herein, but the various changes and modifications may be made without departing from the scope of this novel concept as defined by the following claims.
Table I
Alloy composition
(Weight percent)
Solidification
Alloy mode Cr W Mo Ta Nb Al Tl Co C B Zr Hf Ni
MAR-M200 CC 9 12.5 -- -- 1 5 2 10 0.15 0.015 0.05 -- Balance
CG 9 12 -- -- 1 5 2 10 0.15 0.015 0.05 1.5 Balance
SC 9 12 -- -- 1 5 2 -- -- -- -- -- Balance
MAR-M247 CC 8.4 10 0.65 3.1 -- 5.5 1.1 10 0.15 0.015 0.06 1.4 Balance
CG 8.4 10 0.6 3 -- 5.5 1 10 0.15 0.015 0.06 1.4 Balance
SC 9 10.5 1 3.3 -- 5.8 1.2 -- -- -- -- -- Balance
IN-939 CC 22.5 2 -- 1.4 1 1.9 3.7 19 0.15 0.01 0.010 -- Balance
CG 22.5 2 -- 1.4 1 1.9 3.7 19 0.15 0.01 0.010 -- Balance
SC 22.5 2 -- 1.4 1 1.9 3.7 19 -- -- -- -- Balance
IN-792 CC 12.2 3.8 1.9 3.9 -- 3.5 4.1 9 0.12 0.015 0.06 0.5 Balance
CG 12.2 3.8 1.9 3.9 -- 3.5 4.1 9 0.12 0.015 0.07 1.2 Balance
SC 12.5 3.8 1.9 4.0 -- 3.5 4.0 9 -- -- -- -- Balance
CC-Conventionally Cast ; CG-Columnar Grained ; SC-Single Crystal
Table II
Alloy heat treatment
Solidification
Alloy mode Heat treatment
MAR-M200 CC 1090 C/4 hrs+871 C/32 hrs
CG 1204 C/12 hrs + 1080 C/4 hrs+871 C/32 hrs
SC 1301 C/4 hrs+1080 C/4 hrs +871 C/32 hrs
MAR-M247 CC 1080 C/4 hrs+871 C/20 hrs
CG 1232 C/2 hrs+ 982 C/5 hrs+871 C/20 hrs
SC 1316 C/2 hrs+1323 C/2 hrs+982 C/5 hrs+871 C/20 hrs
IN-939 CC 1160 C/4 hrs+1000 C/6 hrs+900 C/24 hrs+700 C/16 hrs
CG 1160 C/4 hrs+1000 C/6 hrs+900 C/24 hrs+700 C/16 hrs
SC 1232 C/4 hrs+1080 C/4 hrs+871 C/32 hrs
IN-792 CC 1121 C/2 hrs+816 C/24 hrs
CG 1204 C/10 hrs+1220 C/2 hrs+1080 C/4 hrs+816 C/24 hrs
SC 1246 C/4 hrs+1080 C/4 hrs+871 C/32 hrs
CC-Conventionaly Cast : CG-Columnar Grained ; SC-Single Crystal Table III
Effect of solidification mode on creep-rupture properties
Time to 1% Life Rupture
Solidification Tempera- Stress 1% creep Creep ratio life Rupture Life ratio
Alloy mode* ture ( C) (MPa) (hrs) SC/CC SC/CG (hrs) SC/CC SC/CG
MAR-M200 CC 871 413.7 19 60
CG 49 190
SC 114 6.0 2.3 385 6.4 2.0
CC 982 220.64 11 32
CG 20 60
SC 53 4.8 2.7 171 5.3 2.9
MAR-M247 CC 982 206.85 -- 75
CG -- 122
SC -- 210 2.8 1.7
IN-939 CC 871 262.01 -- 150
CG -- 230
SC -- 260 1.7 1.1
IN-792 CC 871 344.7 17 60
CG 47 304
SC 208 12.2 4.4 1192 19.9 3.9
CC 982 186.16 7 22
CG 17 121
SC 91 13.0 5.4 334 15.2 2.8 *CC-Conventionally Cast ; CG-Columnar Grained ; SC-Single Crystal
Claims (2)
1. A high strength nickel base superalloy article characterized in consisting essentially of 9.514% Cr7-11% Co, 1-2.5% Mo, 3-6% W,3-6% Ta,3-4% Al3-5% Ti, O-1% Nb balance essentially nickel with the sum of Al+Ti being from about 6.5 to 8%, said alloy being in the form of a single crystal and thereby exhibiting a substantially enhanced rupture life at elevated temperatures relative to similar alloys in conventionally cast form.
2. An article according to claim 1, characterized in that it has been heat treated and which exhibits a rupture life improvement of at least 10 X relative to similar articles in conventionally cast form.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US33600281A | 1981-12-30 | 1981-12-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2112812A true GB2112812A (en) | 1983-07-27 |
| GB2112812B GB2112812B (en) | 1985-10-16 |
Family
ID=23314160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08236691A Expired GB2112812B (en) | 1981-12-30 | 1982-12-23 | High strength corrosion resistant nickel base single crystal article |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPS58120758A (en) |
| CA (1) | CA1339811C (en) |
| DE (1) | DE3248134A1 (en) |
| FR (1) | FR2519033A1 (en) |
| GB (1) | GB2112812B (en) |
| IL (1) | IL67502A (en) |
| IT (1) | IT1155093B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2153848A (en) * | 1984-02-10 | 1985-08-29 | United Technologies Corp | High strength hot corrosion resistant single crystals |
| US5100484A (en) * | 1985-10-15 | 1992-03-31 | General Electric Company | Heat treatment for nickel-base superalloys |
| US5154884A (en) * | 1981-10-02 | 1992-10-13 | General Electric Company | Single crystal nickel-base superalloy article and method for making |
| US5399313A (en) * | 1981-10-02 | 1995-03-21 | General Electric Company | Nickel-based superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries |
| US6074602A (en) * | 1985-10-15 | 2000-06-13 | General Electric Company | Property-balanced nickel-base superalloys for producing single crystal articles |
| US6086688A (en) * | 1997-07-28 | 2000-07-11 | Alcan International Ltd. | Cast metal-matrix composite material and its use |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4597809A (en) * | 1984-02-10 | 1986-07-01 | United Technologies Corporation | High strength hot corrosion resistant single crystals containing tantalum carbide |
| FR2643085B1 (en) * | 1989-02-10 | 1991-05-10 | Onera (Off Nat Aerospatiale) | NICKEL-BASED SUPERALLOY FOR INDUSTRIAL TURBINE BLADES |
| US5403546A (en) * | 1989-02-10 | 1995-04-04 | Office National D'etudes Et De Recherches/Aerospatiales | Nickel-based superalloy for industrial turbine blades |
| JP2657096B2 (en) * | 1989-05-16 | 1997-09-24 | 三菱マテリアル株式会社 | Precipitation strengthened Ni-based single crystal cast alloy |
| JP6216881B2 (en) | 2013-11-14 | 2017-10-18 | ゼネラル・エレクトリック・カンパニイ | Laminated production of single crystal alloy parts |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB929687A (en) * | 1961-02-28 | 1963-06-26 | Mond Nickel Co Ltd | Improvements relating to nickel-chromium-cobalt alloys |
| US3494709A (en) * | 1965-05-27 | 1970-02-10 | United Aircraft Corp | Single crystal metallic part |
| US3619182A (en) * | 1968-05-31 | 1971-11-09 | Int Nickel Co | Cast nickel-base alloy |
| US4116723A (en) * | 1976-11-17 | 1978-09-26 | United Technologies Corporation | Heat treated superalloy single crystal article and process |
| US4764225A (en) * | 1979-05-29 | 1988-08-16 | Howmet Corporation | Alloys for high temperature applications |
| GB2073774B (en) * | 1980-03-13 | 1983-07-06 | Rolls Royce | Alloy suitable for making single-crustal castings and a casting made thereof |
| IL65897A0 (en) * | 1981-10-02 | 1982-08-31 | Gen Electric | Single crystal nickel-base superalloy,article and method for making |
-
1982
- 1982-12-09 CA CA000417395A patent/CA1339811C/en not_active Expired - Fee Related
- 1982-12-17 IL IL67502A patent/IL67502A/en unknown
- 1982-12-23 GB GB08236691A patent/GB2112812B/en not_active Expired
- 1982-12-24 FR FR8221748A patent/FR2519033A1/en active Pending
- 1982-12-27 DE DE19823248134 patent/DE3248134A1/en active Granted
- 1982-12-27 JP JP57234997A patent/JPS58120758A/en active Pending
- 1982-12-30 IT IT25044/82A patent/IT1155093B/en active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5154884A (en) * | 1981-10-02 | 1992-10-13 | General Electric Company | Single crystal nickel-base superalloy article and method for making |
| US5399313A (en) * | 1981-10-02 | 1995-03-21 | General Electric Company | Nickel-based superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries |
| GB2153848A (en) * | 1984-02-10 | 1985-08-29 | United Technologies Corp | High strength hot corrosion resistant single crystals |
| US5100484A (en) * | 1985-10-15 | 1992-03-31 | General Electric Company | Heat treatment for nickel-base superalloys |
| US6074602A (en) * | 1985-10-15 | 2000-06-13 | General Electric Company | Property-balanced nickel-base superalloys for producing single crystal articles |
| US6086688A (en) * | 1997-07-28 | 2000-07-11 | Alcan International Ltd. | Cast metal-matrix composite material and its use |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS58120758A (en) | 1983-07-18 |
| IT1155093B (en) | 1987-01-21 |
| IT8225044A1 (en) | 1984-06-30 |
| CA1339811C (en) | 1998-04-14 |
| DE3248134C2 (en) | 1989-06-08 |
| GB2112812B (en) | 1985-10-16 |
| DE3248134A1 (en) | 1983-07-07 |
| IL67502A (en) | 1986-01-31 |
| IL67502A0 (en) | 1983-05-15 |
| FR2519033A1 (en) | 1983-07-01 |
| IT8225044A0 (en) | 1982-12-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PE20 | Patent expired after termination of 20 years |
Effective date: 20021222 |