CA1339811C - High strenght corrosion resistant nickel base single crystal article - Google Patents
High strenght corrosion resistant nickel base single crystal articleInfo
- Publication number
- CA1339811C CA1339811C CA000417395A CA417395A CA1339811C CA 1339811 C CA1339811 C CA 1339811C CA 000417395 A CA000417395 A CA 000417395A CA 417395 A CA417395 A CA 417395A CA 1339811 C CA1339811 C CA 1339811C
- Authority
- CA
- Canada
- Prior art keywords
- weight
- single crystal
- article
- nickel base
- superalloy
- 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.)
- Expired - Fee Related
Links
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)
- Inorganic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Chemically Coating (AREA)
- Powder Metallurgy (AREA)
- Adornments (AREA)
Abstract
Disclosed is the improvement in the mechanical properties of a particular nickel base superalloy which is obtainable through the preparation of the material with a modified composition, in single crystal form and with heat treatment. Such single crystals, of a particular composition, display elevated temperature rupture lives which are at least 10X of that displayed by conventionally cast alloys of similar compositions.
Description
13398t 1 High Strength Corrosion Resistant Nickel Base Single Crystal Article Technical Field This invention relates to the field of nickel base superalloy articles such as gas turbine compo-nents which are both resistant to corrosion and are capable of operating at high temperatures. This in-vention also relates to the field of single crystal superalloy articles.
Background Art Increasing demands for efficiency in gas turbine engines have resulted in d~m~nfl.s 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 4,116,723 describes a heat treatment applicable to single crystal super-alloy 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.
~H-7499 ~ 3398 1 Disclosure of Invention Alloys in the composition range 9.5-14% Cr, 7-11% Co, 1-2.5% Mo, 3-6% W, 3-6% Ta, 3-4% Al, 3-5%
Ti balance essentially nickel are provided with im-proved mechanical properties through fabrication ofthe 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 10X improvement in rupture life in comparison to alloys of similar composition which have been conventionally solidified to produce a equiaxed polycrystalline structure.
Other features and advantages will be apparent from the specification and claims which illustrate an embodiment of the invention.
Best Mode For Carrying Out 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 (conventio-nally cast) form, columnar grain (directionally soli-dified) form and single crystal (directionally soli-dified) form. The alloys tested were MAR-M200, MAR-M247, IN 939 and IN 792 (trade marks). 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 compo-~33981 1 -3~
sition 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 sur-prising and unexpected benefits which derive from the fabrication of the modified IN 792 alloy in single crystal form. For the MAR-M200, ~R-M247 and IN 939 alloys the ratio of rupture life of the single crystal samples to the conventional cast samples averaged 4.1X, however for the case of the IN 792, the ratio of single crystal rupture life to 25 conventionally cast rupture life was more than 17X
(average o~ 1600~F/50 ksi and 1800~F/27 ksi tests) Tnis degree of improvement is surprising and un-expected. 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 m ~ a ~ ~ m o ~ O
~D ~ I O O ~9 1~ ..
o o I _I I O o o o i o o I o o 1 o o o o o o o o o o _ o o o I o o I a~
-I U --I ~ r ~ ~ o ,1 -~ ~ -.
Ho ~
o h o o ~ 1 i i ~ ~ ~ O
o o o , ~ . . . . . . . . ,~, .
..
~ ~ u c~ ~ u ~ u u ~ ~ u ~ ~
~: o ~ c~ u u u~ u u u~ u u u~ c o ~
o l ~
,¢ I¢ ~ H H U
0 U~
S SS
~D
o ~
~ O O O
O ~ o o cn cs~ o o ~ ~ U~
U~ + + + +
~ ~q 0 0 U~ 0 0 U~
S ~ h ~ h S~
~1 S
S
~ ~ O er ~r ~ er ~
O ~ ~4 h ~ E4 .~ O 14 00 0 0 0 0 G u~o O O O O ~J ~ r ) r-- O~~'1 O O O u-, ~) ~ a~ o t~
+ + >1 + + + + + + +
u~ ~n 0 u~
0 ~ 0 ~ 0 ~ ~ S ~ ~ ~ S --I
E~ ~ ~ ~ o ~r ~ ~.
:~: ~ 140 E~ 14 ~ 14 h 14 1~4 140 14 ~n o U~o O o O o o oO UO
O ~--In O '~ ~ ~ ~ Ino ~ ~
~: ~O O~ t-- O ~ ~ ~ ~ t'O ~ I' t!: ~ ~1 C ~D ~ ~ oc~ CO C~ N C~
H + +
H E~ + + + + + + + ++ + '' U~ 0 ~
0 m ul u~ 0 un 0m ~ tn a S ~ h S ~ ~
S S SSS SSS S S --o 1 ¢ .O O O O O O O O O O Q O S-u~ r~ ~) ~) O O O O O O ~ ~
~ cc~\~ I' r~ u~) o ~ ~ u~ 10 o r-- C
~ ~ ~ ~ ~ o u o ~
tJ 0 ~ ~ u ~ ~ u ~ u u ~ u ~ u u u u~ u u u~ u u c~ u u u~
~ o ~
o u~ c -~
o l ~ r' ; l l ~~ ~ z z u H H U
, o o a~
~D
O
~ ~ ~ ~ x l_ r.~
r D
0 0 0 ~ ~ O _~ ~ ~ o o o o o ~4 ~; O
'~
4 ~ _~
a) ~ . . . . .
) N ~ ~r U') V
~0 1~ 0 o oo C~ ~
o ~ C~ r~
H a H ~ $ D--~L ~ l~ ~ ~ r'l O ~) 1- 0 O ~ .Cr~l ~ ~ 1 1 1 1 1 1~1 ~ 0 H ~ I C
H
H U~
~: D 0 ~ -I ~ o ~ o co o 1 C u~
v~ ~
E4 _ O
- O ~ C) ~15 0 _~ ,D o o ~ ~ ~ ~
u~
*
~D
, ~ u u u~ U U u~ U U U~ ~ U cq U U u~
~ o o o ~ -u~ o ~
o l ~ r' H Z U
t33981 1 evidence of other superalloys. For purposes of de-fining the invention results, it appears that a minimum lOX improvement in creep rupture life will be obtained.
A similar conclusion is reached when one con-siders the time to 1% creep. In this case, based on the two MAR M alloys, one would expect an average improvement of 5.4X 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 12.6X. Again, this is a disproportionate and unexpec-ted 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 main-tained in this invention.
A heat treatment as described in U.S. 4,116,723 is preferred in order to obtain the maximum increase in properties. Such a heat treatment involves solution-ing of the gamma prime phase and homogenization of thecast structure at a temperature above the gamma prime solvus (2250~F for the invention composition) followed by one or more aging treatments at a lower temperature.
It should be understood that the invention is not limited to the particular embodiments shown and described herein, but that various changes and modifi-cations may be made without departing from the spirit and scope of this novel concept as defined by the following claims.
Background Art Increasing demands for efficiency in gas turbine engines have resulted in d~m~nfl.s 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 4,116,723 describes a heat treatment applicable to single crystal super-alloy 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.
~H-7499 ~ 3398 1 Disclosure of Invention Alloys in the composition range 9.5-14% Cr, 7-11% Co, 1-2.5% Mo, 3-6% W, 3-6% Ta, 3-4% Al, 3-5%
Ti balance essentially nickel are provided with im-proved mechanical properties through fabrication ofthe 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 10X improvement in rupture life in comparison to alloys of similar composition which have been conventionally solidified to produce a equiaxed polycrystalline structure.
Other features and advantages will be apparent from the specification and claims which illustrate an embodiment of the invention.
Best Mode For Carrying Out 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 (conventio-nally cast) form, columnar grain (directionally soli-dified) form and single crystal (directionally soli-dified) form. The alloys tested were MAR-M200, MAR-M247, IN 939 and IN 792 (trade marks). 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 compo-~33981 1 -3~
sition 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 sur-prising and unexpected benefits which derive from the fabrication of the modified IN 792 alloy in single crystal form. For the MAR-M200, ~R-M247 and IN 939 alloys the ratio of rupture life of the single crystal samples to the conventional cast samples averaged 4.1X, however for the case of the IN 792, the ratio of single crystal rupture life to 25 conventionally cast rupture life was more than 17X
(average o~ 1600~F/50 ksi and 1800~F/27 ksi tests) Tnis degree of improvement is surprising and un-expected. 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 m ~ a ~ ~ m o ~ O
~D ~ I O O ~9 1~ ..
o o I _I I O o o o i o o I o o 1 o o o o o o o o o o _ o o o I o o I a~
-I U --I ~ r ~ ~ o ,1 -~ ~ -.
Ho ~
o h o o ~ 1 i i ~ ~ ~ O
o o o , ~ . . . . . . . . ,~, .
..
~ ~ u c~ ~ u ~ u u ~ ~ u ~ ~
~: o ~ c~ u u u~ u u u~ u u u~ c o ~
o l ~
,¢ I¢ ~ H H U
0 U~
S SS
~D
o ~
~ O O O
O ~ o o cn cs~ o o ~ ~ U~
U~ + + + +
~ ~q 0 0 U~ 0 0 U~
S ~ h ~ h S~
~1 S
S
~ ~ O er ~r ~ er ~
O ~ ~4 h ~ E4 .~ O 14 00 0 0 0 0 G u~o O O O O ~J ~ r ) r-- O~~'1 O O O u-, ~) ~ a~ o t~
+ + >1 + + + + + + +
u~ ~n 0 u~
0 ~ 0 ~ 0 ~ ~ S ~ ~ ~ S --I
E~ ~ ~ ~ o ~r ~ ~.
:~: ~ 140 E~ 14 ~ 14 h 14 1~4 140 14 ~n o U~o O o O o o oO UO
O ~--In O '~ ~ ~ ~ Ino ~ ~
~: ~O O~ t-- O ~ ~ ~ ~ t'O ~ I' t!: ~ ~1 C ~D ~ ~ oc~ CO C~ N C~
H + +
H E~ + + + + + + + ++ + '' U~ 0 ~
0 m ul u~ 0 un 0m ~ tn a S ~ h S ~ ~
S S SSS SSS S S --o 1 ¢ .O O O O O O O O O O Q O S-u~ r~ ~) ~) O O O O O O ~ ~
~ cc~\~ I' r~ u~) o ~ ~ u~ 10 o r-- C
~ ~ ~ ~ ~ o u o ~
tJ 0 ~ ~ u ~ ~ u ~ u u ~ u ~ u u u u~ u u u~ u u c~ u u u~
~ o ~
o u~ c -~
o l ~ r' ; l l ~~ ~ z z u H H U
, o o a~
~D
O
~ ~ ~ ~ x l_ r.~
r D
0 0 0 ~ ~ O _~ ~ ~ o o o o o ~4 ~; O
'~
4 ~ _~
a) ~ . . . . .
) N ~ ~r U') V
~0 1~ 0 o oo C~ ~
o ~ C~ r~
H a H ~ $ D--~L ~ l~ ~ ~ r'l O ~) 1- 0 O ~ .Cr~l ~ ~ 1 1 1 1 1 1~1 ~ 0 H ~ I C
H
H U~
~: D 0 ~ -I ~ o ~ o co o 1 C u~
v~ ~
E4 _ O
- O ~ C) ~15 0 _~ ,D o o ~ ~ ~ ~
u~
*
~D
, ~ u u u~ U U u~ U U U~ ~ U cq U U u~
~ o o o ~ -u~ o ~
o l ~ r' H Z U
t33981 1 evidence of other superalloys. For purposes of de-fining the invention results, it appears that a minimum lOX improvement in creep rupture life will be obtained.
A similar conclusion is reached when one con-siders the time to 1% creep. In this case, based on the two MAR M alloys, one would expect an average improvement of 5.4X 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 12.6X. Again, this is a disproportionate and unexpec-ted 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 main-tained in this invention.
A heat treatment as described in U.S. 4,116,723 is preferred in order to obtain the maximum increase in properties. Such a heat treatment involves solution-ing of the gamma prime phase and homogenization of thecast structure at a temperature above the gamma prime solvus (2250~F for the invention composition) followed by one or more aging treatments at a lower temperature.
It should be understood that the invention is not limited to the particular embodiments shown and described herein, but that various changes and modifi-cations may be made without departing from the spirit and scope of this novel concept as defined by the following claims.
Claims (5)
1. A high strength nickel base superalloy article consisting essentially of 9.5-14 weight % Cr, 7-11 weight % Co, 1-2.5 weight % Mo, 3-6 weight % W, 3-6 weight % Ta, 3-4 weight % Al, 3-5 weight % Ti, 0-1 weight % Cb, balance essentially nickel with the sum of Al + Ti being from about 6.5 to 8 weight %, 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 as in claim 1 which has been heat treated and which exhibits a rupture life at elevated temperatures at least 10X that of the same alloy (but containing small additions of C, B and Zr) in conventionally cast form.
3. A high strength nickel base superalloy capable of being cast as a single crystal, consisting essentially of by weight:
Cr 9.5 - 12 Mo 1 - 2.5 Ti 3 - 5 Al 3 - 4 Co 7 - 11 Ta 3 - 6 Cb 0 - 1 Ni plus balance impurities.
Cr 9.5 - 12 Mo 1 - 2.5 Ti 3 - 5 Al 3 - 4 Co 7 - 11 Ta 3 - 6 Cb 0 - 1 Ni plus balance impurities.
4. A cast article of the superalloy of claim 3, having a heat treated single crystal structure.
5. The method of making a cast and heat treated single crystal article of the nickel base superalloy comprising the steps of:
a) providing a superalloy of the composition of claim 3;
b) melting and directionally solidifying the superalloy to produce a single crystal article;
c) heat treating the article to develop a gamma prime structure within the article.
a) providing a superalloy of the composition of claim 3;
b) melting and directionally solidifying the superalloy to produce a single crystal article;
c) heat treating the article to develop a gamma prime structure within the article.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US33600281A | 1981-12-30 | 1981-12-30 | |
| US336,002 | 1981-12-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1339811C true CA1339811C (en) | 1998-04-14 |
Family
ID=23314160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000417395A Expired - Fee Related CA1339811C (en) | 1981-12-30 | 1982-12-09 | High strenght 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) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US5154884A (en) * | 1981-10-02 | 1992-10-13 | General Electric Company | Single crystal nickel-base superalloy article and method for making |
| GB2153848B (en) * | 1984-02-10 | 1987-09-16 | United Technologies Corp | High strength hot corrosion resistant single crystals |
| US4597809A (en) * | 1984-02-10 | 1986-07-01 | United Technologies Corporation | High strength hot corrosion resistant single crystals containing tantalum carbide |
| US6074602A (en) * | 1985-10-15 | 2000-06-13 | General Electric Company | Property-balanced nickel-base superalloys for producing single crystal articles |
| US5100484A (en) * | 1985-10-15 | 1992-03-31 | General Electric Company | Heat treatment for nickel-base superalloys |
| US5403546A (en) * | 1989-02-10 | 1995-04-04 | Office National D'etudes Et De Recherches/Aerospatiales | Nickel-based superalloy for industrial turbine blades |
| FR2643085B1 (en) * | 1989-02-10 | 1991-05-10 | Onera (Off Nat Aerospatiale) | 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 |
| US6086688A (en) * | 1997-07-28 | 2000-07-11 | Alcan International Ltd. | Cast metal-matrix composite material and its use |
| WO2015119692A2 (en) | 2013-11-14 | 2015-08-13 | General Electric Company | Layered manufacturing of single crystal alloy components |
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
Also Published As
| Publication number | Publication date |
|---|---|
| GB2112812A (en) | 1983-07-27 |
| IT1155093B (en) | 1987-01-21 |
| DE3248134A1 (en) | 1983-07-07 |
| IL67502A (en) | 1986-01-31 |
| IT8225044A0 (en) | 1982-12-30 |
| IT8225044A1 (en) | 1984-06-30 |
| GB2112812B (en) | 1985-10-16 |
| FR2519033A1 (en) | 1983-07-01 |
| JPS58120758A (en) | 1983-07-18 |
| IL67502A0 (en) | 1983-05-15 |
| DE3248134C2 (en) | 1989-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4209348A (en) | Heat treated superalloy single crystal article and process | |
| US4222794A (en) | Single crystal nickel superalloy | |
| US4116723A (en) | Heat treated superalloy single crystal article and process | |
| Erickson | A new, third-generation, single-crystal, casting superalloy | |
| US4371404A (en) | Single crystal nickel superalloy | |
| US4981644A (en) | Nickel-base superalloy systems | |
| US5006163A (en) | Turbine blade superalloy II | |
| US4207098A (en) | Nickel-base superalloys | |
| US3832167A (en) | Nickel alloy with good stress-rupture strength | |
| US6054096A (en) | Stable heat treatable nickel superalloy single crystal articles and compositions | |
| EP0577316A2 (en) | Single crystal nickel-based superalloy | |
| JP2004332061A (en) | HIGHLY OXIDATION RESISTANT Ni BASED SUPERALLOY, AND GAS TURBINE COMPONENT | |
| US3459545A (en) | Cast nickel-base alloy | |
| CA1339811C (en) | High strenght corrosion resistant nickel base single crystal article | |
| CA2729117A1 (en) | Ni-based single crystal superalloy and component obtained from the same | |
| US5077004A (en) | Single crystal nickel-base superalloy for turbine components | |
| GB2235697A (en) | Nickel-base superalloys | |
| US5167732A (en) | Nickel aluminide base single crystal alloys | |
| US5516380A (en) | NiAl intermetallic alloy and article with improved high temperature strength | |
| US4597809A (en) | High strength hot corrosion resistant single crystals containing tantalum carbide | |
| EP1394278A1 (en) | Reduced-tantalum superalloy composition and article made therefrom, and method for selecting a reduced-tantalum superalloy | |
| AU630623B2 (en) | An improved article and alloy therefor | |
| US5330711A (en) | Nickel base alloys for castings | |
| GB2110240A (en) | Nickel base superalloy | |
| GB1592237A (en) | Heat treated superalloy single crystal article and process |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |