CA1209827A - Overlay coatings with high yttrium contents - Google Patents
Overlay coatings with high yttrium contentsInfo
- Publication number
- CA1209827A CA1209827A CA000407900A CA407900A CA1209827A CA 1209827 A CA1209827 A CA 1209827A CA 000407900 A CA000407900 A CA 000407900A CA 407900 A CA407900 A CA 407900A CA 1209827 A CA1209827 A CA 1209827A
- Authority
- CA
- Canada
- Prior art keywords
- coating
- coatings
- superalloy
- nickel
- 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.)
- Expired
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
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
-
- 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
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
-
- 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
-
- 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
- C30B33/00—After-treatment of single crystals or homogeneous polycrystalline material with defined structure
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Mechanical Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Inorganic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Physical Vapour Deposition (AREA)
Abstract
Overlay Coatings With High Yttrium Contents Abstract Improved coating compositions are described for the protection of superalloys at elevated temperatures. The coatings of the NiCrAlY or NiCoCrAlY type are signifi-cantly improved by the use of higher levels of yttrium.
Description
8~7 Description Overlay Coat;ngs With High Yttrium Contents Technical Field . .
~ This invention relates to improved NiCrAlY or NiCoCrAlY coatings which are particularly useful in the circumstance where the coating is applied to a hafnium free superalloy substrate. The essence of the invention is to increase the yttrium level in the coating to a level in excess of that previously used.
., - 10 Background Art NiCrAlY and NiCoCrAlY type coatings derive their protective capability from their ability to form (and repeatedly reform) a thin layer of alumina on their outer surface. It is this alumina layer which resists oxida-- 15 tion and hot corrosion attack. Oxygen active elements : ~
such as yttrium are added to the coatings to promote ad-herence of the alumina and to retard its tendency to spall. Hafnium can also be added to improve alumina ad-herence.
. .
-- 20 The prior art did not anticipate this invention, appaxently because of the sequence of developments in the superalloy and coatings field. In the beginning, supexalloys were used in the so called equiaxed form and were used either uncoated or coated with the simple coat-ings such as aluminide coatings. As performance require-ments increased, there were parallel improvements in the superalloy and coating areas1 in the superalloy area substantial improvements were obtained through the de-: EH-7174 ~d~
., ~$~327
~ This invention relates to improved NiCrAlY or NiCoCrAlY coatings which are particularly useful in the circumstance where the coating is applied to a hafnium free superalloy substrate. The essence of the invention is to increase the yttrium level in the coating to a level in excess of that previously used.
., - 10 Background Art NiCrAlY and NiCoCrAlY type coatings derive their protective capability from their ability to form (and repeatedly reform) a thin layer of alumina on their outer surface. It is this alumina layer which resists oxida-- 15 tion and hot corrosion attack. Oxygen active elements : ~
such as yttrium are added to the coatings to promote ad-herence of the alumina and to retard its tendency to spall. Hafnium can also be added to improve alumina ad-herence.
. .
-- 20 The prior art did not anticipate this invention, appaxently because of the sequence of developments in the superalloy and coatings field. In the beginning, supexalloys were used in the so called equiaxed form and were used either uncoated or coated with the simple coat-ings such as aluminide coatings. As performance require-ments increased, there were parallel improvements in the superalloy and coating areas1 in the superalloy area substantial improvements were obtained through the de-: EH-7174 ~d~
., ~$~327
-2~
velopment of directional solidificat;on in which the superalloy is caused to solidify with elongated grains which are crystallographically oriented~ This is de-scribed in U.S. patent 3,26~,505 which is af,signed to the assignee of the present application. In the coating area at about the same time the MCrAlY type overlay coat~
ings were developedO Such coatings are substantially more protective than the previously used aluminide coat-ingsO U.S. patents 3,542,530, 3,676,085, 3,754,303 and
velopment of directional solidificat;on in which the superalloy is caused to solidify with elongated grains which are crystallographically oriented~ This is de-scribed in U.S. patent 3,26~,505 which is af,signed to the assignee of the present application. In the coating area at about the same time the MCrAlY type overlay coat~
ings were developedO Such coatings are substantially more protective than the previously used aluminide coat-ingsO U.S. patents 3,542,530, 3,676,085, 3,754,303 and
3,928,026 relate to MCrAlY overlay coatingsO
Despite the prom~se of directional solidification, significant problems were encountered in the area of transverse ductility. It was found that the grain boundaries separating the orientated elongated grains were notably weak in the direction transverse to the axis of elongation. This problem was overcome through the addition of small amounts of hafnium to the alloy (.5-2~ Hf) as described in U.S. patent 3,711,337 which is also assigned to the present assignee.
Because of the devalopment of hafnium modified directional solidified articles and MCrAlY overlay coat~
ings in the same laboratory at about the same time, it was natural that they would be used in combination with each other. It is also natural that highly demanding applications, specifically first stage turbine blades, would involve the use of both hafnium modified directional solidified substrates and MCrAlY overlay coatings.
The MCrAlY coatings were optimized, as to composition, on directionally solidified hafnium contAin;ng columnar grain substrates. It was found that yttrium in levels greater than about .5 or .7 percent by weight produced undesirable low melting point phases at the coating substrate interface, apparently phases based on yttrium and hafnium.
~2~8;~
An advancement beyond columnar grain articles is the use of similar ~ut more ~dvanced solidi~icatisn techniques to produce single crystal articles as de-scribed in U.S. patent 3,4Y4,70~. Such single crystal articles are free from internal grain boundaries and hence do not suffer from the transverse ductility prob~
lem encountered .in the case of columnar grain articles~
Consequently, there is no need to add hafnium to the alloys for ductility improvements and in fact it has been found desirable to elim.inate hafnium so as to im-prove the heat treatability of single crystal superalloy articles. This subject is discussed in U.S. patent
Despite the prom~se of directional solidification, significant problems were encountered in the area of transverse ductility. It was found that the grain boundaries separating the orientated elongated grains were notably weak in the direction transverse to the axis of elongation. This problem was overcome through the addition of small amounts of hafnium to the alloy (.5-2~ Hf) as described in U.S. patent 3,711,337 which is also assigned to the present assignee.
Because of the devalopment of hafnium modified directional solidified articles and MCrAlY overlay coat~
ings in the same laboratory at about the same time, it was natural that they would be used in combination with each other. It is also natural that highly demanding applications, specifically first stage turbine blades, would involve the use of both hafnium modified directional solidified substrates and MCrAlY overlay coatings.
The MCrAlY coatings were optimized, as to composition, on directionally solidified hafnium contAin;ng columnar grain substrates. It was found that yttrium in levels greater than about .5 or .7 percent by weight produced undesirable low melting point phases at the coating substrate interface, apparently phases based on yttrium and hafnium.
~2~8;~
An advancement beyond columnar grain articles is the use of similar ~ut more ~dvanced solidi~icatisn techniques to produce single crystal articles as de-scribed in U.S. patent 3,4Y4,70~. Such single crystal articles are free from internal grain boundaries and hence do not suffer from the transverse ductility prob~
lem encountered .in the case of columnar grain articles~
Consequently, there is no need to add hafnium to the alloys for ductility improvements and in fact it has been found desirable to elim.inate hafnium so as to im-prove the heat treatability of single crystal superalloy articles. This subject is discussed in U.S. patent
4,116,723 which is assigned to the present assignee~
The present invention arises ~rom the belated ap~
- 15 preciation that the hafnium in the substrate material played a s.ignificant role in enhancing coating perform-ance as well as in improving transverse ductility and that the previously developed NiCrAlY and MiCoCrAlY
coatings can be significantly improved.
Disclosure of Invention The coating compositions of the present invention have the following broad composition ranges: 10-35%
chromium, 8-20% aluminum, 0~30~ chromium, 1.1-3.0~
yttrium, balance essentially nickel. Through the use of higher yttrium levels than those previously used in this type of coating, improved oxidation resistance re sults. The coatings have particular utility on sub-strates which are free from intentional additions of hafnium~
Other features and advantages will be apparent from the specification and claims and from the accompanying drawings which illustrate an em~odiment of the invention.
Brief Description of Drawings ~ The figures shows coating life as a function o~
yttrium level for two different coat~ngs.
Best Mode For Carrying Out The Invention The basis of this invention is the discovery that under certain circumstances, increasing the amount of yttrium in a NiCoCrAlY coating over that taught in the prior art can be beneficial. The circumstance ~n ~hich this high yttrium NiCoCrAlY coating is particularly beneficial is when the coating is applied to hafnium free substrates. Table 1 lists composition ranges for the coatings of the present invention.
Broad ~ Prè~fer~ea Nickel Balance Balance Cobalt 0~30 15-25 Chromium 10-35 15-25 Aluminum 8-20 10-20 Yttrium 1.1-3.0 1~1-3O0 2~
These co~positions ~ide Pnh~n~ ooating n~;~A~;~n resistance and ~re simil~r to the NiCoCr~1~ composition ~escribed in U.S. patent 3,928',026 except for the higher yttrium levels, The i`nvention com,positions are suited ' 5 for the protection of nlckeI base superalloy articles.
It is known in the art that under certain circumstances other additions to NiCoCrAlY coatings can be beneficial.
, For example, U.S. patent 4,034,142 suggests the addition ::
of silicon to MCrAlY coatings while U.S. patent 3,918,139 suggests the addition of platinum and similar noble metals '' to NiCoCrAlY coatingsO The present invention can be ',: applied to the modified NiCoCrAlY coatings described in these references~ It is also envisioned that tantalum (0-10%) can be aaded to the high yttrium MCrAlY coatings lS for improved properties without significantly affecting the beneficial effect supplied ~y the high yttrium con~
tent of the present invention~
The coating compositions previously described may , be applied to a variety of substrate types using dif-': 20 ferent application techniques. Various considerations affect the selection of substrate and coating technique and different benefits can result. The greatest benefit ,, results when the high yttrium NiCoCrAlY coatings of the invention are applied to substrates which are free from - 25 intentional additions of hafnium. Such substrates may , be either of conventionally cast polycrystalline form or ,'' directionally soli~ified columnar grain form, or di-'' rectionally solidified single crystal form. The columnar grain form is not likely because, to date, hafnium has ' 30 been found to be necessary to promote adequate transverse ,' grain boundary ductility in columnar grain articles.
" Nonetheless if one had a ~afnium free columnar grain '' article, the invention coating would be highly pro~
', tective to it. High yttrium coatings will protect ha~ni-35 num free substrates independent of coating deposition technique employed.
The figure shows the effect of yttrium content on oxidation life of an NiCoCr~lY coating material as well as a silicon modified Ni~CoCrAlY coating material D The nom;nal composition by weight of the NiCoCrAlY material was 22% cobalt, 18% chrom~um, 12.5% aluminum, varying amounts of yttrium and balance nickel and the nominal composition by weight of the modified silicon NiCoCrAlY
composition was 22% cobalt, ~8% chromium, 12~5~ aluminum, 1.5% silicon, varying amounts of yttrium and balance nickel. All tests were run on a single crystal substrate having a nominal composition of by weight 10% chromium,
The present invention arises ~rom the belated ap~
- 15 preciation that the hafnium in the substrate material played a s.ignificant role in enhancing coating perform-ance as well as in improving transverse ductility and that the previously developed NiCrAlY and MiCoCrAlY
coatings can be significantly improved.
Disclosure of Invention The coating compositions of the present invention have the following broad composition ranges: 10-35%
chromium, 8-20% aluminum, 0~30~ chromium, 1.1-3.0~
yttrium, balance essentially nickel. Through the use of higher yttrium levels than those previously used in this type of coating, improved oxidation resistance re sults. The coatings have particular utility on sub-strates which are free from intentional additions of hafnium~
Other features and advantages will be apparent from the specification and claims and from the accompanying drawings which illustrate an em~odiment of the invention.
Brief Description of Drawings ~ The figures shows coating life as a function o~
yttrium level for two different coat~ngs.
Best Mode For Carrying Out The Invention The basis of this invention is the discovery that under certain circumstances, increasing the amount of yttrium in a NiCoCrAlY coating over that taught in the prior art can be beneficial. The circumstance ~n ~hich this high yttrium NiCoCrAlY coating is particularly beneficial is when the coating is applied to hafnium free substrates. Table 1 lists composition ranges for the coatings of the present invention.
Broad ~ Prè~fer~ea Nickel Balance Balance Cobalt 0~30 15-25 Chromium 10-35 15-25 Aluminum 8-20 10-20 Yttrium 1.1-3.0 1~1-3O0 2~
These co~positions ~ide Pnh~n~ ooating n~;~A~;~n resistance and ~re simil~r to the NiCoCr~1~ composition ~escribed in U.S. patent 3,928',026 except for the higher yttrium levels, The i`nvention com,positions are suited ' 5 for the protection of nlckeI base superalloy articles.
It is known in the art that under certain circumstances other additions to NiCoCrAlY coatings can be beneficial.
, For example, U.S. patent 4,034,142 suggests the addition ::
of silicon to MCrAlY coatings while U.S. patent 3,918,139 suggests the addition of platinum and similar noble metals '' to NiCoCrAlY coatingsO The present invention can be ',: applied to the modified NiCoCrAlY coatings described in these references~ It is also envisioned that tantalum (0-10%) can be aaded to the high yttrium MCrAlY coatings lS for improved properties without significantly affecting the beneficial effect supplied ~y the high yttrium con~
tent of the present invention~
The coating compositions previously described may , be applied to a variety of substrate types using dif-': 20 ferent application techniques. Various considerations affect the selection of substrate and coating technique and different benefits can result. The greatest benefit ,, results when the high yttrium NiCoCrAlY coatings of the invention are applied to substrates which are free from - 25 intentional additions of hafnium. Such substrates may , be either of conventionally cast polycrystalline form or ,'' directionally soli~ified columnar grain form, or di-'' rectionally solidified single crystal form. The columnar grain form is not likely because, to date, hafnium has ' 30 been found to be necessary to promote adequate transverse ,' grain boundary ductility in columnar grain articles.
" Nonetheless if one had a ~afnium free columnar grain '' article, the invention coating would be highly pro~
', tective to it. High yttrium coatings will protect ha~ni-35 num free substrates independent of coating deposition technique employed.
The figure shows the effect of yttrium content on oxidation life of an NiCoCr~lY coating material as well as a silicon modified Ni~CoCrAlY coating material D The nom;nal composition by weight of the NiCoCrAlY material was 22% cobalt, 18% chrom~um, 12.5% aluminum, varying amounts of yttrium and balance nickel and the nominal composition by weight of the modified silicon NiCoCrAlY
composition was 22% cobalt, ~8% chromium, 12~5~ aluminum, 1.5% silicon, varying amounts of yttrium and balance nickel. All tests were run on a single crystal substrate having a nominal composition of by weight 10% chromium,
5~ cobalt, 4~ tungsten, 1.4% titanium, 12% tantalum, 5 aluminum balance essentially nickel.
The coatings were applied by electron beam vapor physical deposition process. Testing was performed in a cyclic burner rig operated at a peak temperature of 2100F. The coating life results were ad~usted to re-flect differences in coating th~ckness.
The effect of increased yttrium is seen to be a significant increase in coating life. For example in the NiCoCrAlY case, increa~ing the yttrium content from 1% to 2% increases the coating life from about 825 hours to about 1290 hours, an increase of more than 50%.
~nother class of substrates to which the invention coating can be applied are those substrates which con-tain hafnium. If the invention coatings are applied to sub~trates which contain hafnium, the formation o low melting phases at the substrate-coating interface may be a problem. This can be min;mi2ed if the coating is applied by a plasma spray process. Plasma spray deposit-ed coatings invariably contain a sufficient quantity of oxygen to oxidize the substrate hafnium which is near the coating-substrate interface~ Once the hafnium is :~l2~8~7 oxidized, it is stable and will not form the deleterious low melting point phase. Thus the deposition o~ the in-vention coatings ~y plasma spraying onto hafnium con taining substrates does not present melting point prob-lems.
Wherl MCrAlY coatings are applied by ~apor deposition to hafnium cont~;n;ng substrates, hafnium from the sub-strate diffuses into the coating and improves its per-formance. However, when MCrAlY coatings are applied by plasma spraying to hafnium contA;ning substrates, the oxygen which is present as yttrium and aluminum oxides in the coating prevents the hafnium from di~fusing suf-ficiently to the surface of the coating to improve its performance. Instead, the diffusing hafnium reduces the o~her oxides, ~alumina and yttria) and forms stable haf-nium oxides, and as a result, no coating improvement re-sults.
By using the yttrium-rich c~ating of the present invention, it is possible to compensate for the loss of the substrate hafnium "effect" on plasma sprayed coat~
ings. The increased ~ttrium substitutes for the missing hafnium in promoting good adherence of the coatings' protective alumina scale. Thus plasma spray coating durability is enhanced even on hafnium-containing sub stratesO
It should be understood that the invention is not limited to the particular em~odiments shown and described herein, but that various changes and modifications may be made without departing from the spirit and scope of this novel concept as defined by the following claims~
The coatings were applied by electron beam vapor physical deposition process. Testing was performed in a cyclic burner rig operated at a peak temperature of 2100F. The coating life results were ad~usted to re-flect differences in coating th~ckness.
The effect of increased yttrium is seen to be a significant increase in coating life. For example in the NiCoCrAlY case, increa~ing the yttrium content from 1% to 2% increases the coating life from about 825 hours to about 1290 hours, an increase of more than 50%.
~nother class of substrates to which the invention coating can be applied are those substrates which con-tain hafnium. If the invention coatings are applied to sub~trates which contain hafnium, the formation o low melting phases at the substrate-coating interface may be a problem. This can be min;mi2ed if the coating is applied by a plasma spray process. Plasma spray deposit-ed coatings invariably contain a sufficient quantity of oxygen to oxidize the substrate hafnium which is near the coating-substrate interface~ Once the hafnium is :~l2~8~7 oxidized, it is stable and will not form the deleterious low melting point phase. Thus the deposition o~ the in-vention coatings ~y plasma spraying onto hafnium con taining substrates does not present melting point prob-lems.
Wherl MCrAlY coatings are applied by ~apor deposition to hafnium cont~;n;ng substrates, hafnium from the sub-strate diffuses into the coating and improves its per-formance. However, when MCrAlY coatings are applied by plasma spraying to hafnium contA;ning substrates, the oxygen which is present as yttrium and aluminum oxides in the coating prevents the hafnium from di~fusing suf-ficiently to the surface of the coating to improve its performance. Instead, the diffusing hafnium reduces the o~her oxides, ~alumina and yttria) and forms stable haf-nium oxides, and as a result, no coating improvement re-sults.
By using the yttrium-rich c~ating of the present invention, it is possible to compensate for the loss of the substrate hafnium "effect" on plasma sprayed coat~
ings. The increased ~ttrium substitutes for the missing hafnium in promoting good adherence of the coatings' protective alumina scale. Thus plasma spray coating durability is enhanced even on hafnium-containing sub stratesO
It should be understood that the invention is not limited to the particular em~odiments shown and described herein, but that various changes and modifications may be made without departing from the spirit and scope of this novel concept as defined by the following claims~
Claims (5)
1. A coated gas turbine component displaying enhanced resistance to oxidation which comprises a nickel base superalloy substrate, said superalloy being free from intentional additions of Hf, and a coating consisting essentially of 15-25% Co, 15-25%
Cr, 10-20% Al, 1.1-3.0% Y, balance nickel, on the substrate.
Cr, 10-20% Al, 1.1-3.0% Y, balance nickel, on the substrate.
2. A coated gas turbine component as in claim 1, in which the substrate is a single crystal article.
3. Method for improving the oxidation resistance of nickel base superalloys, which are free from inten-tional additions of Hf, which comprises applying a coating material to the surface, said coating material consisting essentially of 15-25% Cr, 10-20% Al, 1.1-3.0% y, 15-25% Co, balance essentially nickel.
4. A coating composition capable of providing superior protection to superalloy substrates (which are free from intentional additions of Hf) consisting essentially of 15-25% Cr, 10-20% Al, 1.1-3.0% Y, 15-25% Co, balance essentially nickel.
5. A coated gas turbine component displaying enhanced resistance to oxidation which comprises a superalloy substrate, said superalloy containing .1-2% Hf, and a plasma sprayed coating on the sub-strate, said coating consisting essentially of 10-35%
Cr, 8-20% Al, 1.1-3.0% Y, 0-30% Co, balance nickel.
Cr, 8-20% Al, 1.1-3.0% Y, 0-30% Co, balance nickel.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US28995381A | 1981-08-05 | 1981-08-05 | |
| US289,953 | 1981-08-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1209827A true CA1209827A (en) | 1986-08-19 |
Family
ID=23113894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000407900A Expired CA1209827A (en) | 1981-08-05 | 1982-07-23 | Overlay coatings with high yttrium contents |
Country Status (6)
| Country | Link |
|---|---|
| JP (1) | JPS5837146A (en) |
| CA (1) | CA1209827A (en) |
| DE (1) | DE3229285A1 (en) |
| FR (1) | FR2511043B1 (en) |
| GB (1) | GB2103656B (en) |
| IL (1) | IL66443A (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4743514A (en) * | 1983-06-29 | 1988-05-10 | Allied-Signal Inc. | Oxidation resistant protective coating system for gas turbine components, and process for preparation of coated components |
| US4677035A (en) * | 1984-12-06 | 1987-06-30 | Avco Corp. | High strength nickel base single crystal alloys |
| DE3612568A1 (en) * | 1986-04-15 | 1987-10-29 | Bbc Brown Boveri & Cie | HIGH TEMPERATURE PROTECTIVE LAYER |
| JP2773050B2 (en) * | 1989-08-10 | 1998-07-09 | シーメンス アクチエンゲゼルシヤフト | Heat-resistant and corrosion-resistant protective coating layer |
| US5582635A (en) * | 1990-08-10 | 1996-12-10 | Siemens Aktiengesellschaft | High temperature-resistant corrosion protection coating for a component in particular a gas turbine component |
| US5401307A (en) * | 1990-08-10 | 1995-03-28 | Siemens Aktiengesellschaft | High temperature-resistant corrosion protection coating on a component, in particular a gas turbine component |
| JP2003147464A (en) | 2001-11-02 | 2003-05-21 | Tocalo Co Ltd | Member with high-temperature strength |
| DE102005053531A1 (en) * | 2005-11-08 | 2007-05-10 | Man Turbo Ag | Heat-insulating protective layer for a component within the hot gas region of a gas turbine |
| US7754342B2 (en) * | 2005-12-19 | 2010-07-13 | General Electric Company | Strain tolerant corrosion protecting coating and spray method of application |
| GB2443283A (en) * | 2006-10-26 | 2008-04-30 | Gen Electric | Rub coating for gas turbine engine compressors |
| US7879459B2 (en) * | 2007-06-27 | 2011-02-01 | United Technologies Corporation | Metallic alloy composition and protective coating |
| WO2010070982A1 (en) | 2008-12-16 | 2010-06-24 | 旭硝子株式会社 | Filmed metal member for float glass manufacturing equipment and float glass manufacturing method |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL136758C (en) * | 1963-10-21 | 1900-01-01 | ||
| US3494709A (en) * | 1965-05-27 | 1970-02-10 | United Aircraft Corp | Single crystal metallic part |
| US3542530A (en) * | 1968-05-23 | 1970-11-24 | United Aircraft Corp | Nickel or cobalt base with a coating containing iron chromium and aluminum |
| US3711337A (en) * | 1970-12-16 | 1973-01-16 | United Aircraft Corp | Columnar-grained nickel-base superalloy castings |
| US3676085A (en) * | 1971-02-18 | 1972-07-11 | United Aircraft Corp | Cobalt base coating for the superalloys |
| US3873347A (en) * | 1973-04-02 | 1975-03-25 | Gen Electric | Coating system for superalloys |
| US3928026A (en) * | 1974-05-13 | 1975-12-23 | United Technologies Corp | High temperature nicocraly coatings |
| US3918139A (en) * | 1974-07-10 | 1975-11-11 | United Technologies Corp | MCrAlY type coating alloy |
| FR2315387A1 (en) * | 1975-06-23 | 1977-01-21 | Cabot Corp | Nickel alloy contg. chromium, aluminium and yttrium - with high thermal shock resistance, and useful for coating nickel or cobalt base superalloys |
| DE2528241A1 (en) * | 1975-06-25 | 1977-01-13 | Cabot Corp | Nickel alloy contg. chromium, aluminium and yttrium - with high thermal shock resistance, and useful for coating nickel or cobalt base superalloys |
| US3964877A (en) * | 1975-08-22 | 1976-06-22 | General Electric Company | Porous high temperature seal abradable member |
| US4029477A (en) * | 1975-10-29 | 1977-06-14 | General Electric Company | Coated Ni-Cr base dispersion-modified alloy article |
| US4034142A (en) * | 1975-12-31 | 1977-07-05 | United Technologies Corporation | Superalloy base having a coating containing silicon for corrosion/oxidation protection |
| US4116723A (en) * | 1976-11-17 | 1978-09-26 | United Technologies Corporation | Heat treated superalloy single crystal article and process |
| US4101713A (en) * | 1977-01-14 | 1978-07-18 | General Electric Company | Flame spray oxidation and corrosion resistant superalloys |
| JPS55161041A (en) * | 1979-05-29 | 1980-12-15 | Howmet Turbine Components | Covering material |
-
1982
- 1982-07-23 CA CA000407900A patent/CA1209827A/en not_active Expired
- 1982-08-02 IL IL66443A patent/IL66443A/en not_active IP Right Cessation
- 1982-08-02 FR FR8213454A patent/FR2511043B1/en not_active Expired
- 1982-08-02 GB GB08222226A patent/GB2103656B/en not_active Expired
- 1982-08-05 DE DE19823229285 patent/DE3229285A1/en active Granted
- 1982-08-05 JP JP57137165A patent/JPS5837146A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| IL66443A (en) | 1985-11-29 |
| GB2103656A (en) | 1983-02-23 |
| DE3229285C2 (en) | 1988-11-24 |
| JPH0372706B2 (en) | 1991-11-19 |
| FR2511043A1 (en) | 1983-02-11 |
| GB2103656B (en) | 1985-06-26 |
| DE3229285A1 (en) | 1983-03-24 |
| IL66443A0 (en) | 1982-12-31 |
| JPS5837146A (en) | 1983-03-04 |
| FR2511043B1 (en) | 1987-05-22 |
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Legal Events
| Date | Code | Title | Description |
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| MKEX | Expiry |