GB2322869A - A coated superalloy article - Google Patents
A coated superalloy article Download PDFInfo
- Publication number
- GB2322869A GB2322869A GB9704477A GB9704477A GB2322869A GB 2322869 A GB2322869 A GB 2322869A GB 9704477 A GB9704477 A GB 9704477A GB 9704477 A GB9704477 A GB 9704477A GB 2322869 A GB2322869 A GB 2322869A
- Authority
- GB
- United Kingdom
- Prior art keywords
- superalloy article
- aluminide
- platinum
- rhenium
- coating
- 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- Withdrawn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
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
Abstract
A rhenium-containing nickel superalloy article 10 has a multilayer coating 12 comprising a nickel aluminide layer 14 and a protective coating which may be a platinum aluminide-silicide coating 16. The platinum aluminide-silicide coating 16 is a very good corrosion and oxidation protective coating for the superalloy article 10. The nickel aluminide layer 14 prevents platinum and/or silicon in the platinum aluminide-silicide coating diffusing to the superalloy article 10 to minimise the formation of topologically close packed phases at the interface between the superalloy article 10 and the multilayer coating 12. It is also possible to have a cobalt aluminide layer on cobalt superalloy articles. The nickel aluminide layer 14 is preferably produced by high activity, low temperature, aluminising.
Description
A COATED SUPERALLOY ARTICLE AND A METHOD OF COATING
A SUPERALLOY ARTICLE
The present invention relates to coated superalloy articles and to methods of coating superalloy articles, particularly rhenium-containing nickel and cobalt superalloy turbine blades or turbine vanes.
It is known to produce aluminide-silicide protective coatings on superalloy turbine blades or turbine vanes to extend the service lives of the turbine blades or turbine vanes.
It is known to produce aluminide-silicide coatings on a superalloy article by depositing a silicon filled organic slurry on the superalloy article and then pack aluminising as described in US4310574. The aluminium carries the silicon from the slurry with it as it diffuses into the superalloy. Another method of producing aluminide-silicide coatings is by depositing a slurry containing elemental aluminium and silicon metal powders on a superalloy article and then heating to above 760 0C to melt the aluminium and silicon in the slurry, such that they react with the superalloy and diffuse into the superalloy article as described in US3248251. A further method of producing aluminide-silicide coatings is by repeatedly applying the aluminium and silicon containing slurry and heat treating as described in
US5547770. Another method of producing aluminidesilicide coatings is by applying a slurry of an eutectic aluminium-silicon or a slurry of elemental aluminium and silicon metal powders on a superalloy article and diffusion heat treating to form a surface layer of increased thickness and reduced silicon content, and a layering layer which comprises alternate interleaved layers of aluminide and silicide phases and a diffusing interface layer as described in published EuropeaTh- patent application No. 0619856A.
It is also known to produce platinum aluminidesilicide coatings on a superalloy article by coating the superalloy article with platinum, then heat treating to diffuse the platinum into the superalloy article and then simultaneously diffusing aluminium and silicon from the molten state into the platinum enriched superalloy article as described in published International patent application No. W095/23243A. Another method of producing platinum aluminide-silicide coatings on a superalloy article is by coating the superalloy article with platinum, then heat treating to diffuse the platinum into the superalloy article, a silicon layer is applied and is then aluminised as described in published European patent application No. 0654542A. It is also possible to diffuse the silicon into the superalloy article with the platinum as described in EP0654542A. A further method of producing platinum aluminide-silicide coatings on superalloy articles is by electrophoretically depositing platinum-silicon powder onto the superalloy article, heat treating to diffuse platinum and silicon into the superalloy article, then electrophoretically depositing aluminium and chromium powder and then heat treating to diffuse the aluminium and chromium into the superalloy article as described in US5057196.
It has been found that if a platinum aluminidesilicide coating is produced on a rhenium-containing superalloy article the platinum acts as a diffusion barrier and causes a build-up of the very heavy elements rhenium, tungsten and tantalum beneath the coating. This results in the formation of topologically close packed phases (TCP phases), within the superalloy substrate.
These TCP phases are needle-like rhenium and tungsten rich phases which extend into the substrate. The TCP phases are undesirable because they reduce the useful load bearing area of the superalloy substrate. Also cracking may occur at the interface between the superalloy substrate and the TCP phase leading to decohesion of the platinum aluminide-silicide coating.
Thus the application of a platinum aluminide-silicide coating directly onto a rhenium containing superalloy article is not practical because these TCP phases increase the stress within the rhenium containing superalloy substrate leading to premature failure of the rhenium containing superalloy article.
It has also been found that if an aluminidesilicide coating is produced on a rhenium containing superalloy article that this results in the formation of topologically close packed phases (TCP phases), with the rhenium containing superalloy substrate, especially for aluminide-silicide coatings produced by repeated depositions of slurry and diffusion heat treatments.
These TCP phases are needle-like rhenium and tungsten rich phases which extend into the superalloy substrate.
The TCP phases are undesirable because they reduce the load bearing area of the superalloy substrate. The TCP phases are not as severe in the aluminide-silicide coating as they are in the platinum aluminide-silicide coating. Thus the use of an aluminide-silicide coating directly onto a rhenium containing superalloy article is not as beneficial as it should be because these TCP phases reduce the load bearing area in the rheniumcontaining superalloy substrate leading to premature failure of the rhenium-containing superalloy article.
The invention therefore seeks to provide an aluminide-silicide coating on a rhenium-containing superalloy article with reduced formation, preferably no formation, of the TCP phases.
Accordingly the present invention provides a method of coating a rhenium-containing superalloy article comprising the steps of :
(a) applying a coating comprising aluminium to the rhenium-containing superalloy article and diffusing the aluminium into the rhenium-containing superalloy article to produce a nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article to reduce the formation of TCP phases in the rhenium-containing superalloy article,
(b) and depositing a protective coating on the nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article.
Preferably step (a) comprises aluminising the rhenium-containing superalloy article. Preferably the aluminising is at a temperature of 8000C to 950 C.
Preferably step (b) comprises depositing an aluminide-silicide coating.
Preferably step (b) comprises depositing a platinum aluminide-silicide coating.
Alternatively step (b) may comprise depositing an platinum aluminide coating or a MCrAlY coating, where M is at least one of Ni, Co and Fe.
Preferably step (b) comprises depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, simultaneously diffusing aluminium and silicon from the molten state into the coated rhenium-containing superalloy article.
Alternatively step (b) may comprise depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated rhenium-containing superalloy article.
Alternatively step (b) may comprise depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, diffusing aluminium into the coated rhenium-containing superalloy article.
Preferably the platinum is deposited by electroplating. Preferably the platinum is heat treated at a temperature greater than 100 ooh. Preferably the platinum is heat treated at a temperature of 1120 0C for 1 to 2 hours to diffuse the platinum. Preferably the platinum is deposited to a thickness between 5 and 15 micrometers.
Alternatively step (b) may comprise depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated rhenium-containing superalloy article.
Alternatively step (b) may comprise simultaneously diffusing aluminium and silicon from the molten state into the coated rhenium-containing superalloy article.
Preferably the diffusion of aluminium and silicon is at a temperature in the range 7500C to 1120 0C.
Preferably the simultaneous diffusion of aluminium and silicon from the molten state is repeated at least once more.
The present invention also provides a coated rhenium-containing superalloy article comprising a nickel aluminide, or a cobalt aluminide, layer on the rheniumcontaining superalloy article, and a protective coating on the nickel aluminide or cobalt aluminide layer.
The protective coating may be an aluminide-silicide coating, a platinum aluminide-silicide coating, a platinum aluminide coating or a MCrAlY coating, where M is at least one of Ni, Co and Fe.
The rhenium-containing superalloy article may be a nickel based superalloy article.
The rhenium-containing superalloy article may be a high rhenium-containing nickel based superalloy article.
The rhenium-containing superalloy article may be a single crystal superalloy article.
The rhenium-containing superalloy article may be a turbine blade or a turbine vane.
The platinum aluminide-silicide coating may comprise some silicide phases, the nickel aluminide, or cobalt aluminide, layer comprises some platinum aluminide and the nickel aluminide, or cobalt aluminide1 layer comprises some silicide phases.
The present invention will be more fully described by way of example with reference to the accompanying drawings, in which:
Figure 1 is a cross-sectional view through a coated superalloy article according to the present invention.
Figure 2 is a cross-sectional view through a further coated superalloy article according to the present invention.
Figure 3 is a cross-sectional view through another coated superalloy article according to the present invention.
A rhenium-containing nickel superalloy article 10, for example a gas turbine engine turbine blade or turbine vane, has a multilayer coating 12 as shown in figure 1.
The multi layer coating 12 comprises a nickel aluminide layer 14 on the rhenium-containing nickel superalloy article 10 and a platinum aluminide-silicide coating 16 on the nickel aluminide layer 14. The nickel aluminide layer 14 may contain some platinum aluminide. The platinum aluminide-silicide coating 16 comprises platinum aluminide with some silicide phases.
It is believed that the provision of the nickel aluminide layer 14 between the rhenium-containing nickel superalloy article 10 and the platinum aluminide coating 16 prevents the silicon in the platinum aluminidesilicide coating diffusing to the rhenium-containing nickel superalloy article 10. It is postulated that this is due to the nickel aluminide layer 14 forming a barrier to the diffusion of any element, e.g. platinum and/or silicon which may trigger the formation of the TCP phases in the superalloy article, from the platinum aluminidesilicide coating 16 to the rhenium-containing nickel superalloy article 10. Preferably the nickel aluminide layer 14 prevents platinum and/or silicon diffusing to the rhenium-containing nickel superalloy article 10.
Nickel aluminide is a very strong and stable intermetallic.
The nickel aluminide layer 14 is produced on the rhenium-containing nickel superalloy article 10 by depositing an aluminium coating onto the rheniumcontaining nickel superalloy article 10 and the aluminium is then heat treated to diffuse the aluminium into the rhenium-containing nickel superalloy article 10 to form the nickel aluminide layer 14 on the rhenium-containing nickel superalloy article 10. The aluminium is deposited and diffused by high activity, low temperature, pack aluminising or alternatively by high activity, low temperature, out of pack vapour aluminising or by high activity, low temperature, slurry aluminising. The high activity, low temperature, aluminising process requires a temperature of preferably 8000C to 950 0C for about 5 hours. It may be possible to use lower diffusion temperatures, for example temperatures as low as 7000C or even as low as 6000C, but these will require much longer diffusion times. Alternatively the aluminium is deposited and diffused by low activity, high temperature, aluminising to form the nickel aluminide using pack aluminising, out of pack vapour aluminising or slurry aluminising.
A platinum layer is then deposited on the nickel aluminide layer 14 and the platinum is then heat treated to diffuse the platinum into the nickel aluminide layer 14. The platinum is deposited to a thickness of 5 to 15 micrometers by electroplating, physical vapour deposition or other suitable means. The platinum is heat treated at a temperature greater than 10000C, for example 1 hour at 1120 0C followed by gas fan quenching and ageing for 24 hours at 8450C.
Aluminium and silicon are then deposited and are heat treated to diffuse them into the platinum to form the platinum aluminide-silicide coating 16. The aluminium and silicon are deposited using a slurry comprising aluminium and silicon powders dispersed in a chromate/phosphate binder and the slurry is cured to a solid matrix which holds the metal pigments in contact with the metal surface during the heat treatment. The aluminium and silicon are heat treated at a temperature in the range 7500C to 1120 0C to simultaneously diffuse them from the molten state as described in US3248251 which is incorporated herein by reference. The silicon may be deposited first by spraying a silicon filled slurry and then pack aluminising. The aluminium diffusing into the platinum carries the silicon with it as described in US4310574 which is also incorporated herein by reference. Other suitable methods of depositing and diffusing the aluminium and silicon may be used.
It may be beneficial to repeat the deposition of the aluminium and silicon and the diffusion heat treatment steps to provide a plurality of bands rich in silicon and a plurality of bands rich in aluminium with the silicon rich bands and aluminium rich bands arranged alternately through the depth of the platinum aluminide-silicide coating. This technique is described more fully in published International Patent application No.
W093/23247.
During the diffusion of the silicon and aluminium into the nickel aluminide 14 and platinum coated rhenium containing superalloy article the aluminium reacts with the platinum to form a platinum aluminide coating 16 and the silicon diffuses through the platinum but the nickel aluminide layer forms a barrier to prevent, or reduce the amount of platinum and/or silicon reaching the superalloy article 10. Thus the nickel aluminide layer stops the - platinum and/or silicon diffusing to the rhenium containing superalloy article 10.
Another rhenium-containing nickel superalloy article 20, for example a gas turbine engine turbine blade or turbine vane, according to the present invention has a multilayer coating 22 as shown in figure 2. The multilayer coating 22 comprises a nickel aluminide layer 24 on the rhenium-containing superalloy article 20, and a platinum aluminide coating 26 on the nickel aluminide layer 24.
The multilayer coating 22 is produced on the superalloy article 20 using similar processes as described to produce the multilayer coating 12 on the superalloy article 10. In the platinum aluminising process the platinum is deposited to a similar thickness and by similar methods as for the platinum aluminidesilicide coating already described with reference to figure 1. The aluminising process entails the diffusion of aluminium only into the platinum rather than aluminium and silicon as in .the platinum aluminide-silicide coating.
In tests we have deposited a platinum aluminidesilicide coating onto a high rhenium-containing nickel based single crystal superalloy, for example CMSX1O, and found that the TCP phases are formed at the interface with the superalloy article. CMSX10 is produced by the
Cannon-Muskegon Corporation of 2875 Lincoln Street,
Muskegon, Michigan, MI 49433-0506, USA. CMSX10 has a nominal composition range of 3.5 to 6.5wit% tungsten, 2.0 to 5.0wit% cobalt, 1.8 to 3.Owt% chromium, 5.5 to 6.5wit% rhenium, 5.3 to 6.5wit aluminium, 8.0 to 10.Owt% tantalum, 0.2 to 0.8wt% titanium, 0.25 to 1.swot% molybdenum, 0.02 to 0.05wit% hafnium, 0 to 0.03we niobium, 0 to 0.04wit% carbon and the balance is nickel.
In tests we have deposited a platinum aluminidesilicide coating onto a nickel based superalloy - containing no rhenium, for example MAR-M002, and found that no TCP phases are formed at the interface with the superalloy article. MAR-M002 is produced by the Martin
Marietta Corporation of Bethesda, Maryland, USA. MAR
M002 has a nominal composition of 10with tungsten, 10wtW cobalt, 9wt% chromium, 5.5wit% aluminium, 2.5wit% tantalum, 1.5wit% titanium, 1.5wit% hafnium, 0.015wt% carbon and the balance is nickel.
In tests we have deposited a nickel aluminide coating onto a high rhenium-containing nickel based single crystal superalloy, for example CMSX10, and found that TCP phases are not formed at the interface with the superalloy article. The nickel aluminide was deposited by high activity, low temperature, aluminising.
Thus we believe that the use of the nickel aluminide layer minimises, preferably prevents, the formation of deleterious TCP phases. We believe that the stable nickel aluminide intermetallic phases acts as a barrier to the diffusion of any elements in the platinum aluminide-silicide coating which may trigger the formation of the TCP phases. Thus the formation of deleterious TCP phases at the rhenium-containing superalloy article interface is at least minimised.
The invention is also applicable to other aluminidesilicide coatings where there is a problem of formation of the deleterious topologically close packed phases at the interface between the superalloy article and the aluminide-silicide coating.
One example of this is when the deposition of the aluminium and silicon and the diffusion heat treatment steps are repeated to provide a plurality of bands rich in silicon and a plurality of bands rich in aluminium with the silicon rich bands and aluminium rich bands arranged alternately through the depth of the aluminidesilicide coating. This technique is described more fully in published International Patent application No.
W093/23247.
A rhenium-containing nickel superalloy article 30, for example a gas turbine engine turbine blade or turbine vane, has a multilayer coating 32 as shown in figure 3.
The multilayer coating 32 comprises a nickel aluminide layer 34 on the rhenium-containing nickel superalloy article 30 and an aluminide-silicide coating 36 on the nickel aluminide layer 34. The aluminide-silicide coating 36 comprises alternate silicon rich bands 38 and aluminium rich bands 40.
It is believed that the provision of the nickel aluminide layer 34 between the rhenium-containing nickel superalloy article 30 and the aluminide-silicide coating 36 prevents the silicon in an aluminide-silicide coating 36 diffusing to the rhenium-containing nickel superalloy article 30. It is postulated that this is due to the nickel aluminide layer 34 forming a barrier to the diffusion of silicon from the aluminide-silicide coating 36 to the rhenium-containing nickel superalloy article 30 and thus minimises the amount of the deleterious TCP phases formed in the rhenium-containing nickel superalloy article 30. Preferably the nickel aluminide layer 34 prevents silicon diffusing to the rhenium-containing nickel superalloy article 30. Nickel aluminide is a very strong and stable intermetallic.
In tests we have deposited an aluminide-silicide coating containing a plurality of bands rich in silicon and a plurality of bands rich in aluminium with the silicon rich bands and aluminium rich bands arranged alternately through the depth of the aluminide-silicide coating onto a high rhenium-containing nickel based single crystal superalloy, for example CMSX10, and found that the silicon rich TCP phases are formed at the interface with the superalloy article. CMSX10 is produced by the Cannon-Muskegon Corporation of 2875
Lincoln Street, Muskegon, Michigan, MI 49433-0506, USA.
CMSX10 has a nominal composition range of 3.5 to 6.5wit% tungsten, 2.0 to 5.Owt% cobalt, 1.8 to 3.Owt% chromium, 5.5 to 6.5wit% rhenium, 5.3 to 6.5wt% aluminium, 8.0 to 10.Owt% tantalum, 0.2 to 0.8wt% titanium, 0.25 to 1.5wit% molybdenum, 0.02 to 0.05wok hafnium, 0 to 0.03wt% niobium, 0 to 0.04wt% carbon and the balance is nickel.
The invention has been described with reference to a nickel superalloy article, it is also possible to apply the invention to a cobalt superalloy in which case a cobalt aluminide layer will be formed under the platinum aluminide-silicide coating rather than a nickel aluminide layer.
The nickel based superalloy is preferably a high rhenium-content nickel based superalloy, for example
CMSX10, but may be a low rhenium-content nickel based superalloy, for example CMSX4, or any other nickel based single crystal superalloy which suffers from the formation of the TCP phases. The high rhenium-containing nickel superalloys contain more than 4wt% rhenium. The superalloy article may be a gas turbine blade or gas turbine vane.
The invention is also applicable to other aluminising processes where topologically close packed phases are formed. The invention is also applicable to other protective coatings where topologically close packed phases are formed, we have found that the TCP phases are formed on high rhenium-containing nickel superalloys, for example CMSX10, which have MCrAlY overlay coatings.
In the case of aluminide-silicide coatings, particularly platinum aluminide-silicide coatings it may be possible to introduce at least one of chromium, titanium and tantalum into the aluminide layer. The chromium, titanium and tantalum react with any silicon diffusing through the aluminide layer to form stable intermetallics which tie up the silicon to minimise the formation of the silicon rich TCP phases.
Claims (29)
1. A method of coating a rhenium-containing superalloy article comprising the steps of :
(a) applying a coating comprising aluminium to the rhenium-containing superalloy article and diffusing the aluminium into the rhenium-containing superalloy article to produce a nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article to reduce the formation of TCP phases in the rhenium-containing superalloy article,
(b) and subsequently depositing a protective coating on the nickel aluminide, or cobalt aluminide, layer on the rhenium-containing superalloy article.
2. A method as claimed in claim 1 wherein step (a) comprises aluminising the rhenium-containing superalloy article.
3. A method as claimed in claim 2 wherein the aluminising is carried out at a temperature within the range 8000C to 9500C.
4. A method as claimed in claim 1, claim 2 or claim 3 wherein step (b) comprises depositing an aluminidesilicide coating.
5. A method as claimed in claim 4 wherein step (b) comprises depositing a platinum aluminide-silicide coating.
6. A method as claimed in claim 1, claim 2 or claim 3 wherein step (b) comprises depositing a platinum aluminide coating.
7. A method as claimed in claim 1, claim 2 or claim 3 wherein step (b) comprises depositing a MCrAlY coating, where M is at least one of Ni, Co and Fe.
8. A method as claimed in claim 5 wherein step (b) comprises depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rheniumcontaining superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, simultaneously diffusing aluminium and silicon from the molten state into the coated rheniumcontaining superalloy article.
9. A method as claimed in claim 5 wherein step (b) comprises depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rheniumcontaining superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated rhenium-containing superalloy article.
10. A method as claimed in claim 6 wherein step (b) comprises depositing the platinum onto the nickel aluminide, or cobalt aluminide, layer on the rheniumcontaining superalloy article, heat treating to diffuse the platinum into the nickel aluminide or cobalt aluminide layer, diffusing aluminium into the coated rhenium-containing superalloy article.
11. A method as claimed in claim 8, claim 9 or claim 10 wherein the platinum is deposited by electroplating.
12. A method as claimed in claim 8, claim 9, claim 10 or claim 11 wherein the platinum is heat treated at a temperature greater than 10000C.
13. A method as claimed in claim 12 wherein the platinum is heat treated at a temperature of 11200C for 1 to 2 hours to diffuse the platinum.
14. A method as claimed in claim 8, claim 9, claim 10, claim 11 , claim 12 or claim 13 wherein the platinum is deposited to a thickness between 5 and 15 micrometers.
15. A method as claimed in claim 3 wherein step (b) comprises depositing silicon and then depositing aluminium and diffusing the silicon and aluminium into the coated rhenium-containing superalloy article.
16. A method as claimed in claim 3 wherein step (b) comprises simultaneously diffusing aluminium and silicon from the molten state into the coated rhenium-containing superalloy article.
17. A method as claimed in claim 8, claim 9, claim 15 or claim 16 wherein the diffusion of aluminium and silicon is at a temperature in the range 7500C to 11200C.
18. A method as claimed in claim 8, claim 9, claim 15 or claim 16 wherein the simultaneous diffusion of aluminium and silicon from the molten state is repeated at least once more.
19. A method of coating a rhenium-containing superalloy article substantially as hereinbefore described with reference to the accompanying drawings.
20. A coated rhenium-containing superalloy article comprising a nickel aluminide, or a cobalt aluminide, layer on the rhenium-containing superalloy article, and a protective coating on the nickel aluminide or cobalt aluminide layer.
21. A coated superalloy article as claimed in claim 20 wherein the protective coating is an aluminide-silicide coating.
22. A coated superalloy article as claimed in claim 21 wherein the protective coating is a platinum aluminidesilicide coating.
23. A coated superalloy article as claimed in claim 20 wherein the protective coating is a platinum aluminide coating.
24. A coated superalloy article as claimed in claim 20 wherein the protective coating is a MCrA1Y coating, where
M is at least one of Ni, Co and Fe.
25. A coated superalloy article as claimed in any of claims 20 to 24 wherein the superalloy article is a nickel based superalloy article.
26. A coated superalloy article as claimed in any of claims 20 to 25 wherein the superalloy article is a high rhenium-containing nickel based superalloy article.
27. A coated superalloy article as claimed in claim 26 where in the superalloy article is a single crystal superalloy article.
28. A coated superalloy article as claimed in any of claims 20 to 27 wherein the superalloy article is a turbine blade or a turbine vane.
29. A coated rhenium containing superalloy article substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9704477A GB2322869A (en) | 1997-03-04 | 1997-03-04 | A coated superalloy article |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9704477A GB2322869A (en) | 1997-03-04 | 1997-03-04 | A coated superalloy article |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9704477D0 GB9704477D0 (en) | 1997-04-23 |
| GB2322869A true GB2322869A (en) | 1998-09-09 |
Family
ID=10808682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9704477A Withdrawn GB2322869A (en) | 1997-03-04 | 1997-03-04 | A coated superalloy article |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2322869A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6461746B1 (en) * | 2000-04-24 | 2002-10-08 | General Electric Company | Nickel-base superalloy article with rhenium-containing protective layer, and its preparation |
| CN1105789C (en) * | 1999-01-12 | 2003-04-16 | 中国人民解放军第5719工厂 | Low temperature aluminizing technology for steel blade of aircraft engine |
| EP1335017A1 (en) * | 2002-02-08 | 2003-08-13 | General Electric Company | Nickel-base superalloy article substrate having aluminide coating thereon, and its fabrication |
| EP1652959A1 (en) | 2004-10-29 | 2006-05-03 | General Electric Company | Method for depositing gamma-prime nickel aluminide coatings |
| US10934860B2 (en) | 2016-06-21 | 2021-03-02 | Rolls-Royce Plc | Gas turbine engine component with protective coating |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111334759B (en) * | 2020-03-05 | 2023-01-17 | 广东省科学院新材料研究所 | Application of diffusion barrier material, high-temperature coating, preparation method and application of high-temperature coating, and hot-end part of gas turbine |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3955935A (en) * | 1974-11-27 | 1976-05-11 | General Motors Corporation | Ductile corrosion resistant chromium-aluminum coating on superalloy substrate and method of forming |
| US4639399A (en) * | 1985-11-26 | 1987-01-27 | The United States Of America As Represented By The Secretary Of The Navy | Nickel oxide, ceramic insulated, high temperature coating |
| US5077141A (en) * | 1984-12-06 | 1991-12-31 | Avco Corporation | High strength nickel base single crystal alloys having enhanced solid solution strength and methods for making same |
| EP0545661A2 (en) * | 1991-12-05 | 1993-06-09 | General Electric Company | Substrate stabilization of diffusion aluminide coated nickel-based superalloys |
| US5270123A (en) * | 1992-03-05 | 1993-12-14 | General Electric Company | Nickel-base superalloy and article with high temperature strength and improved stability |
| EP0654542A1 (en) * | 1993-11-19 | 1995-05-24 | Walbar Inc. | Improved platinum group silicide modified aluminide coating process and products |
| GB2285632A (en) * | 1985-08-19 | 1995-07-19 | Garrett Corp | Thermal barrier coating system for superalloy components |
| WO1995030779A1 (en) * | 1994-05-10 | 1995-11-16 | United Technologies Corporation | Method for improving oxidation and spalling resistance of diffusion aluminide coatings |
| US5514482A (en) * | 1984-04-25 | 1996-05-07 | Alliedsignal Inc. | Thermal barrier coating system for superalloy components |
| EP0718420A1 (en) * | 1994-12-24 | 1996-06-26 | Rolls Royce Plc | A method of applying a thermal barrier coating to a superalloy article and a thermal barrier coating |
| EP0733723A1 (en) * | 1995-03-21 | 1996-09-25 | Howmet Corporation | Thermal barrier coating system |
-
1997
- 1997-03-04 GB GB9704477A patent/GB2322869A/en not_active Withdrawn
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3955935A (en) * | 1974-11-27 | 1976-05-11 | General Motors Corporation | Ductile corrosion resistant chromium-aluminum coating on superalloy substrate and method of forming |
| US5514482A (en) * | 1984-04-25 | 1996-05-07 | Alliedsignal Inc. | Thermal barrier coating system for superalloy components |
| US5077141A (en) * | 1984-12-06 | 1991-12-31 | Avco Corporation | High strength nickel base single crystal alloys having enhanced solid solution strength and methods for making same |
| GB2285632A (en) * | 1985-08-19 | 1995-07-19 | Garrett Corp | Thermal barrier coating system for superalloy components |
| US4639399A (en) * | 1985-11-26 | 1987-01-27 | The United States Of America As Represented By The Secretary Of The Navy | Nickel oxide, ceramic insulated, high temperature coating |
| EP0545661A2 (en) * | 1991-12-05 | 1993-06-09 | General Electric Company | Substrate stabilization of diffusion aluminide coated nickel-based superalloys |
| US5270123A (en) * | 1992-03-05 | 1993-12-14 | General Electric Company | Nickel-base superalloy and article with high temperature strength and improved stability |
| EP0654542A1 (en) * | 1993-11-19 | 1995-05-24 | Walbar Inc. | Improved platinum group silicide modified aluminide coating process and products |
| WO1995030779A1 (en) * | 1994-05-10 | 1995-11-16 | United Technologies Corporation | Method for improving oxidation and spalling resistance of diffusion aluminide coatings |
| EP0718420A1 (en) * | 1994-12-24 | 1996-06-26 | Rolls Royce Plc | A method of applying a thermal barrier coating to a superalloy article and a thermal barrier coating |
| EP0733723A1 (en) * | 1995-03-21 | 1996-09-25 | Howmet Corporation | Thermal barrier coating system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1105789C (en) * | 1999-01-12 | 2003-04-16 | 中国人民解放军第5719工厂 | Low temperature aluminizing technology for steel blade of aircraft engine |
| US6461746B1 (en) * | 2000-04-24 | 2002-10-08 | General Electric Company | Nickel-base superalloy article with rhenium-containing protective layer, and its preparation |
| US6632480B2 (en) | 2000-04-24 | 2003-10-14 | General Electric Company | Nickel-base superalloy article with rhenium-containing protective layer, and its preparation |
| EP1335017A1 (en) * | 2002-02-08 | 2003-08-13 | General Electric Company | Nickel-base superalloy article substrate having aluminide coating thereon, and its fabrication |
| EP1652959A1 (en) | 2004-10-29 | 2006-05-03 | General Electric Company | Method for depositing gamma-prime nickel aluminide coatings |
| US7357958B2 (en) | 2004-10-29 | 2008-04-15 | General Electric Company | Methods for depositing gamma-prime nickel aluminide coatings |
| US10934860B2 (en) | 2016-06-21 | 2021-03-02 | Rolls-Royce Plc | Gas turbine engine component with protective coating |
Also Published As
| Publication number | Publication date |
|---|---|
| GB9704477D0 (en) | 1997-04-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0821076B1 (en) | A method of aluminising a superalloy | |
| US6299986B1 (en) | Coated superalloy article and a method of coating a superalloy article | |
| US4152223A (en) | Plasma sprayed MCrAlY coating and coating method | |
| JP3001161B2 (en) | Aluminum coating for super alloy | |
| US4005989A (en) | Coated superalloy article | |
| US4789441A (en) | Metallic protective coatings and method of making | |
| EP1616979B1 (en) | Applying a protective coating on a substrate and method for manufacturing the protective layer | |
| JP3973171B2 (en) | High temperature alloy article with discrete additional protective coating and method of manufacturing the same | |
| US4246323A (en) | Plasma sprayed MCrAlY coating | |
| US4326011A (en) | Hot corrosion resistant coatings | |
| EP2145969A1 (en) | Economic oxidation and fatigue resistant metallic coating | |
| JP4615677B2 (en) | Method for controlling the thickness and aluminum content of diffusion aluminide coatings | |
| EP2417276B1 (en) | Superalloy component, which comprises an aluminide coating, which comprises three layers | |
| EP1144727A1 (en) | Antiabrasion coating | |
| US6521294B2 (en) | Aluminiding of a metallic surface using an aluminum-modified maskant, and aluminum-modified maskant | |
| US4909984A (en) | High temperature protective coating | |
| GB2322869A (en) | A coated superalloy article | |
| GB2322382A (en) | A coated superalloy article | |
| CA2156081C (en) | Diffusion barrier layers | |
| EP3351653A1 (en) | Aluminide diffusion coating system and process for forming an aluminide diffusion coating system | |
| GB2322383A (en) | A coated superalloy article | |
| CN111247312B (en) | Turbine component made of rhenium-containing superalloy and associated manufacturing method | |
| GB2378452A (en) | A metallic article having a protective coating and a method therefor | |
| CN113242913A (en) | Turbine component made of a rhenium and/or ruthenium containing superalloy and associated manufacturing method | |
| EP0064542A1 (en) | Improved interdispersed phase coatings method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |