IL47181A - High temperature nicocraiy coatings - Google Patents
High temperature nicocraiy coatingsInfo
- Publication number
- IL47181A IL47181A IL47181A IL4718175A IL47181A IL 47181 A IL47181 A IL 47181A IL 47181 A IL47181 A IL 47181A IL 4718175 A IL4718175 A IL 4718175A IL 47181 A IL47181 A IL 47181A
- Authority
- IL
- Israel
- Prior art keywords
- nickel
- cobalt
- coating
- chromium
- yttrium
- Prior art date
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
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
-
- 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
- C22C19/052—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 40%
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S428/00—Stock material or miscellaneous articles
- Y10S428/922—Static electricity metal bleed-off metallic stock
- Y10S428/923—Physical dimension
- Y10S428/924—Composite
- Y10S428/926—Thickness of individual layer specified
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12861—Group VIII or IB metal-base component
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12861—Group VIII or IB metal-base component
- Y10T428/12931—Co-, Fe-, or Ni-base components, alternative to each other
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12986—Adjacent functionally defined components
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Physical Vapour Deposition (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
Description
HIGH TEMPERATURE BICoCrALY COATINGS nam mioano!? NiCoCrAlY »» aji The present invention relates to coatings and coated articles and more particularly to coatings for the nickel-and cobalt-base superalloys having high ductility while retaining desirable stability and elevated temperature oxidation and hot corrosion resistance.
Design trends for advanced gas turbine engines are toward ever increasing turbine inlet temperatures, and the demands on turbine materials have increased to the extent where contemporary aluminide coating systems can be the life limiting component of alloy-coating composites.
Coatings are prone to failure by a variety of mechanisms. Aluminide coatings can be, for example, a source of fracture initiation in fatigue. Coating ductility has been found to be an important determinant in. fatigue life since at relatively low temperatures aluminide coatings tend to crack in a brittle manner at low strains in the tensile portions of the fatigue cycle. Although various coatings, such as the CoCrAlY type coatings described in the US patent 3 676 085, the iCrAlY type coatings described in the US patent 3 754 903 and the FeCrAlY type coatings described in the US patent 3 542 530 have in the past provided significant improvements in the lifetimes of the superalloys, further improvements are, of course, desirable. In particular, an improved coating having properties comparable to the conventional coating alloys together with significantly improved ductility would be desirable and useful. Such an improved coating is found in the nickel-cobalt-chromium-aluminum-yttrium system as described herein.
In brief, the present invention relates to a nickel-cobalt-chromium-aluminum-yttrium coating alloy having greatly improved ductility as well as other properties which together render it eminently suitable for use in gas turbine engine hardware and other rigorous environments.
The invention more particularly relates to a high ductility coating alloy which possesses both oxidation-erosion and sulfidatxon resistance and which consists of a particular combination of nickel, cobalt, chromium, aluminum and a reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and the other rare earth elements. The invention contemplates a coating composition consisting essentially of, by weight, 11-487» cobalt, 10-40% chromium, 9-15% aluminum, 0.01-1.0% of a reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and other rare earth elements, balance essentially nickel, the nickel content being at 12-30% chromium, 10-15% aluminum, 0.01-1.0% yttrium, ^ -balance essentially nickel, the nickel content being at least about 15%.
In one preferred embodiment, the coating composition consists essentially of, by weight , about 25-40% cobalt, 14-22% chromium, 13-15% aluminum, 0.01-1.0% yttrium, balance essentially nickel.
In another preferred embodiment, the coating composition consists essentially of, by weight, about 15-35% cobalt, 14-22% chromium, 10-13% aluminum, 0.01-1.0% yttrium, balance essentially nickel.
In order that the invention may be fully understood, reference is made on the following drawings, in which: Figure 1 is a graph which dramatically illustrates the ductility behavior of various nickel-cobalt-chromium-aluird num-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
Figure 2 is a graph showing ductility as a function of temperature of some NiCoCrAlY coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
Figure 3 is a graph illustrating the diffusicnal stability of various nickel-cobalt-chromium-aluminum-yttriu coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
Figure 4 is a graph illustrating the oxidation characteristics of various nickel-cobalt-chromium-aluminum-yttrium, coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
Figure 5 is a graph illustrating the sulfidation charac eristics of various nickel-cobalt-chromium-aluminum-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys.
In the description which follows, reference will be made to various of the conventional or contemporar nickel- base and cobalt-base superalloys. Representative of alloys of this nature are those identified in the industry as follows: NOMINAL COMPOSITION ALLOY DESIGNATION (Percent by weight) B-1900 . 8 Cr, 10 Co, 1 Ti, 6 Al, 6 Mo, .11 C, 4.3 Ta, .15 B, .07 Zr, balance Ni MAR-M302 21.5 Cr, 10 W, 9 Ta, .85 C, .25 Zr, 1 Fe, balance Co TD Cobalt Alloy 20 Ni, 18 Cr, 2 Th02, balance Co TD Cobalt Alloy 20 Ni, 30 Cr, 2 Th02, balance Co IN 100 10 Cr, 15 Co, 4.5 Ti, 5.5 Al, 3 Mo, .17 C, .75 V, .075 Zr, .015 B, balance Ni MAR-M200 9 Cr, 10 Co, 2 Ti, 5 Al, 12.5 W, .15 C, 1 Nb, .05 Zr, .015 B, balance Ni WI 52 . 21 Cr, 1.75 Fe, 11 W, 2(Nb + Ta), .45 C, balance Co It will be appreciated that while the superalloys including those which are directionally solidified, taken as a class, are generally oxidation resistant, it is a necessary and usual practice to coat certain of the components formed therefrom in order to improve their oxidation, sulfidation, erosion and thermal shock resistance and thus extend their operating lives in advanced gas turbine engines.
As noted hereinbefore, the CoCrAlY and NiCrAlY coatings have provided significant improvements in the lifetimes of the superalloys. However, it was found that NiCrAlY coatings, while providing extremely high oxidation resistance and diffusional stability required improvement in sulfidation resistance and that CoCrAlY coatings, while providing extremely high sulfidation resistance required improvement in oxidation resistance and diffusional stability. In an effort to develop a better combination of properties, a variety of overlay coatings was evaluated. It was found that coating alloys of a composition, by weight, of 11-487, cobalt, 10-407» chromium, 9-157Q aluminum 0.01-1.0% reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and the other rare earth elements, balance essentially nickel, the nickel content being at least about 15%, preferably 15-407» cobalt, 12-30% chromium, 10-15% aluminum, 0.01-1.07=> yttrium, balance essentially nickel, the nickel content being at least about 15%, and most preferably (1) 25-40% Co, 14-22% Cr, 13-15% w « dramatically and unexpectedly gave an increase in ductility while providing a satisfactory and adjustable balance of oxidation and hot corrosion resistance as well as acceptably low interdiffusional characteristics. While it had been known that certain of the useful NiCrAlY coatings exhibited a ductility higher than certain of the useful CoCrAlY coatings and it had been surmised therefore that a substitution of some nickel for the cobalt in the CoCrAlY composition might improve ductility, it was surprising and unexpected that the nickel-cobalt-chromium-aluminum-yttrium system as defined above would provide a ductility improvement which was markedly superior to either the NiCrAlY or CoCrAlY.
While not completely understood at the present time, it appears that there is a correlation between coating ductility and the phases present. More specifically, chemistry changes which increase the amount and continuity of the (Ni, Co) solid solution phase, Y , tend to increase coating ductility while chemistry changes which increase the amount and continuity of the (Ni, Co) Al, , Ni^Al, X ' , and Cr, c , tend to decrease ductility. Correlation of coating microstructure with coating chemistry indicates that, in the nickel-cobalt-chromium-aluminum-yttrium system herein described, desirable V - microstruetures are obtained at a higher aluminum content, the increased stability of the - microstructure caused by cobalt additions to NiCrAlY being the result of a significant phases which are precipitated at lower temperatures.
Those skilled in the art will recognize that certain other elements are known to be compatible with the basic chemistry of the present alloys. Accordingly, other elements such as tantalum or hafnium may be advantageously added to the alloy as required in certain applications for modification of the mechanical, diffusional or hot corrosion characteristics of the coating.
In coating the nickel-base and cobalt-base turbine blades and vanes the surfaces to be coated are first thoroughly cleaned free of all dirt, grease and other objectional foreign matter followed by conditioning by abrasive blasting. The coating is achieved by vapor deposition from a suitably heated molten pool of the -4 coating material held in a vacuum chamber at 10 torr or better. The ingot melted and evaporated by electron beam heating has essentially the same chemistry as that of the desired finished coating.
Parts are preferably preheated to J^'7^^^5J& for five, to six minutes before deposition is initiated and this temperature is maintained throughout the coating operation. Deposition time varies somewhat but is controlled to obtain the preferred coating thickness of Subsequent cooling to below Γ0ΙΕΓ2? is accomplished in a nonoxidizing atmosphere. Following the coating step, the parts may be heat treated for one hour at ".Γ'\"~" „ 'Μ. ί·η provide for easier peening.
The coated articles may be dry glass bead peened using .£^iSill£S'¾.≤a diameter beads with an intensity equivalent to 19 N. In general, the peening is conducted in accordance with the provisions of the processing specification AMS 2430» The parts may then be heated to ¾.'¾^^>^ in dry argon, dry hydrogen or vacuum; held at heat for four hours; and cooled in the protective atmosphere at a rate equivalent to air cooling. Blades and vanes so processed exhibit a o. ο -coating thickness, excluding the diffused zone of ¾H-03i SJ 0.1 r>y.r>r\. , Of course, it will be recognized that other methods for applying the coatings may be practiced, such as sputtering, ion plating or plasma spraying, without departing from the intent of the present invention.
Referring to Figure 1, a graph is shown of the unexpected ductility behavior of various nickel-cobalt-chromium- aluminum-yttrium coating alloys as compared to representative CoCrAlY and NiCrAlY coating alloys. The results shown therein were obtained by measuring strain to fracture of coatings deposited on tensile specimens of appropriate superalloys. In particular, Curve A is a plot showing the effects of substituting various amounts of cobalt for nickel in a NiCrAlY alloy having a nominal composition of, by weight, Ni-19Cr-14Al-0.5Y while Curve B is a plot showing the effects of substituting various amounts of composition of, by weight, Ni-19Cr-12.5A1-0.5Y. As is evident from the drawing, dramatic increases in ductility are obtained and it has been found, in general, that NiCoCrAlY, or CoNiCrAlY as the case may be, coating alloys have compositional ranges consisting essentially of, by weight, 11-48% Co, 10-40% Cr, 9-15% Al, 0.1-1.0% reactive metal selected from the group consisting of yttrium, scandium, thorium, lanthanum and the other rare earth elements, balance essentially nickel (at least about 15%), preferably 15-40% Co, 12-30% Cr, 10-15% Al, 0.1-1.0% Y, balance essentially Ni, the nickel content being at least about 15%>, will be effective in this regard. As will be appreciated, with the higher Al content, as shown by Curve A, a generally higher range of cobalt is preferred, a preferred coating consisting essentially of 25-407o Co, 14-22% Cr, 13-15% Al, 0.01-1.0% Y, balance essentially Ni. With lower Al content, as shown by Curve B, a generally lower range of cobalt is preferred, a preferred coating consisting essentially of 15-35% Co, 14-22% Cr, 10-13% Al, 0.01-0.1% Y. In Figure 2, ductility curves for selected coatings show ductility as a function of temperature and indicate the markedly superior tensile cracking resistance of the NiCoCrAlY coatings.
In one series of thermomechanical fatigue tests, a directionally solidified specimen substrate of MAR-M200 (with hafnium) was coated with Ni-24Co-16Cr-12.5A1-0.3Y and pulls the specimen in severe fatigue and temperature cycles which simulate the strain- emperature cycle of a cooled turbine blade. A number of identical substrates were coated with Co-20Cr-12Al-0.5Y and another number with a diffusion aluminide coating. Both the CoCrAlY and the diffusion aluminide coated specimens failed after approximately 1,000 cycles or less on the thermomechanical fatigue machine whereas the NiCoCrAlY coated ^specimen did not fail until afte 1,925 cycles.
Referring to Figures 3-5, a comparison of the inter-diffusional, oxidation resistance and corrosion resistance properties of various NiCoCrAlY alloy coatings is shown.
In the drawings, Ss§¾i2 coatings of NiCoCrAlY alloy consisting essentially of the indicated amounts of cobalt, 18-21% Cr, 13-14% Al and 0.05-0.8% Y were vapor deposited onto B-1900 substrates as well as onto directionally solidified MAR-M200 (plus Hf) substrates (erosion bars) .
In Figure 3, the coated samples were aged 100 hours in air at the indicated temperature. In Figure 4, coated components were subjected to ZQQ&gS cyclic burner-rig oxidation tests (Ρ ίϊ , 29 minutes - forced air cool, one minute, JP 5 fuel used) for up to 2,100 hours (2,030 hours hot time). In Figure 5, coated components were treated under cyclic conditions (L,75Q° , three minutes - 2X102.^, two minutes -cool, two minutes) in a high velocity hot gas stream derived from the combustion of JP 5 jet fuel, with 35 ppm salt/air specimens showed no visual signs of degradation. Based on metallographic examination of specimens from the B QW tests, coating degradation was least for the Ni-32.5Co-20Cr-12Al-0.5Y. Also in the Z: :S3 test, the NiCoCrAlY coating exhibited the least degradation. The extent of degradation of the CoNiCrAlY and CoCrAlY coatings was approximately equal.
The ZSliC s isothermal oxidation test was discontinued at 305 hours. Again the NiCoCrAlY coating showed the least degradation while the CoCrAlY coating showed the most.
The SSS^^ isothermal oxidation test was run to coating failure. Of the three coatings systems evaluated, the NiCoCrAlY composition exhibited the longest life, 226 hours.
The cyclic oxidation and cyclic hot corrosion tests were discontinued at 207 (59 hours hot time) and 204 (58 hours hot time) hours, respectively. Coating failure had not occurred. Essentially no difference was observed in the structure between the three samples in the hot corrosion test. However, in the cyclic oxidation test, the Ni-32.5Co-20Cr-12Al-0.5Y coating exhibited a far greater amount of retained beta than either of the other two.
Examples 15-16 In a series of especially severe engine tests, first stage turbine blades of the alloys indicated were coated as indicated in Table I and run for 297 hours including 2,000 cycles (acceleration to full takeoff power followed power and holding for a period of time) . Over 100 cycles were with water injection (for thrust augmentation) which imposed the severest possible thermal shock to the coatings.
Number Tested Alloy Coating 3-1900 8 & Hf latinum aluminide I! rhodium aluminide 7 I! high temperature pack aluminide 14 It low temperature pack aluminide 56 (I 4 Ni-18Cr-14Al-0.5Y t! Ni-12Cr-14Al-0.5Y 2 M Ni-18Cr-10Al-0„5Y 2 ri Ni-12Cr-12Al-0.5Y I! Ni-18Cr-12Al-0.5Y 3 Direc ionally solidified MA -M200 & Hf Ni-18Cr-12Al-0.5Y B-1900 & Hf Ni-llCo-22Cr-llAl-0,06Y II Ni-20Co-16Cr-ll.5Al-0.05Y 5 While NiCrAlY had not previously cracked in other engine tests and is therefore considered acceptable for most engine conditions, this test was particularly severe and, as shown, only the NiCoCrAlY coated blades were completely free of coating cracks. In similar tests, CoCrAlY coatings consistently cracked.
It has been clearly established that the inventive alloy coatings are effective not only in providing long term oxidation resistance, corrosion resistance and stability but dramatically improved ductility.
What has been set forth above is intended primarily as exemplary to enable those skilled in the art to practice the invention and it should therefore be understood that, within the scope of the appended claims, the invention may be practiced in other ways than as specifically described.
Claims (8)
1. A coating composition for the nickel-base and cobalt-base alloys characterized in that it consists essentially of, by weight, 11-48% cobalt, 10-40% chromium, 9-15% aluminum, 0.01-1.0% of a reactive metal selected from the group consisting of yttrium, scandium:, thorium., lanthanum, and other rare earth elements balance essentially nickel, the nickel content being at least about 15%.
2. A coating composition according to clai 1, characterized in that it consists essentially of, by weight, 15-40% cobalt, 12-30% chromium, 10-15% aluminum, 0.01-1.0% yttrium, balance essentially nickel, the nickel content being at least about 15%
3. coating composition according to claim 1 , characterized in that it consists essentially of, by weight, 25-40% cobalt, 14-22% chromium, 13-15% aluminum, o.01-1.0% yttrium, balance essentially nickel.
4. A coating composition according to claim 1, characterized that it consists essentially of, by weight, 15-35% cobalt, 14-22% chromium, 10-13% aluminum, 0.01-1.0% yttrium, balance essentially nickel.
5. A coating composition according to claim 1, characterized that it consists essentially of, by weight, 32.5% cobalt, 20% chromium, 12% aluminum, 0.5% yttrium, balance essentially nickel.
6. A coating composition according to claim 1, characterized in that it consists essentially of, by weight, 20% nickel, 20% chromium, 12% aluminum, 0.5% yttrium, balance essentially cobalt.
7. A gas turbine engine component comprising a nickel-base or cobalt-base superalloy coated to a thickness of at least about 0.07 mm with. the coating described according to anyone of the claims 1-6.
8. Coating composition according to claims 1-6 for the nickel-base and cofcalt-base alloys as hereinbefore described with reference to the accompanying drawings. ADVOCATE, PATENT ATTORNEY P. O. B. 39251 TEL-AVIV, I SRA E L
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US469186A US3928026A (en) | 1974-05-13 | 1974-05-13 | High temperature nicocraly coatings |
Publications (2)
Publication Number | Publication Date |
---|---|
IL47181A0 IL47181A0 (en) | 1975-08-31 |
IL47181A true IL47181A (en) | 1977-07-31 |
Family
ID=23862796
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
IL47181A IL47181A (en) | 1974-05-13 | 1975-04-28 | High temperature nicocraiy coatings |
Country Status (10)
Country | Link |
---|---|
US (1) | US3928026A (en) |
JP (1) | JPS5919977B2 (en) |
CA (1) | CA1045421A (en) |
CH (1) | CH606454A5 (en) |
DE (1) | DE2520192C2 (en) |
FR (1) | FR2271299B1 (en) |
GB (1) | GB1489796A (en) |
IL (1) | IL47181A (en) |
IT (1) | IT1038126B (en) |
SE (1) | SE410476B (en) |
Families Citing this family (86)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3993454A (en) * | 1975-06-23 | 1976-11-23 | United Technologies Corporation | Alumina forming coatings containing hafnium for high temperature applications |
USRE33876E (en) * | 1975-09-11 | 1992-04-07 | United Technologies Corporation | Thermal barrier coating for nickel and cobalt base super alloys |
US4029477A (en) * | 1975-10-29 | 1977-06-14 | General Electric Company | Coated Ni-Cr base dispersion-modified alloy article |
USRE30995E (en) * | 1977-06-09 | 1982-07-13 | General Electric Company | High integrity CoCrAl(Y) coated nickel-base superalloys |
USRE31339E (en) * | 1977-08-03 | 1983-08-09 | Howmet Turbine Components Corporation | Process for producing elevated temperature corrosion resistant metal articles |
DE2842848A1 (en) * | 1977-10-17 | 1979-04-19 | United Technologies Corp | COVERED OBJECT, IN PARTICULAR SUPER ALLOY GAS TURBINE BLADE |
US4198442A (en) * | 1977-10-31 | 1980-04-15 | Howmet Turbine Components Corporation | Method for producing elevated temperature corrosion resistant articles |
US4275124A (en) * | 1978-10-10 | 1981-06-23 | United Technologies Corporation | Carbon bearing MCrAlY coating |
US4275090A (en) * | 1978-10-10 | 1981-06-23 | United Technologies Corporation | Process for carbon bearing MCrAlY coating |
US4313760A (en) * | 1979-05-29 | 1982-02-02 | Howmet Turbine Components Corporation | Superalloy coating composition |
US4339509A (en) * | 1979-05-29 | 1982-07-13 | Howmet Turbine Components Corporation | Superalloy coating composition with oxidation and/or sulfidation resistance |
US4346137A (en) * | 1979-12-19 | 1982-08-24 | United Technologies Corporation | High temperature fatigue oxidation resistant coating on superalloy substrate |
US4372377A (en) * | 1981-03-16 | 1983-02-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Heat pipes containing alkali metal working fluid |
CA1209827A (en) * | 1981-08-05 | 1986-08-19 | David S. Duvall | Overlay coatings with high yttrium contents |
US4615865A (en) * | 1981-08-05 | 1986-10-07 | United Technologies Corporation | Overlay coatings with high yttrium contents |
US4419416A (en) * | 1981-08-05 | 1983-12-06 | United Technologies Corporation | Overlay coatings for superalloys |
US4514469A (en) * | 1981-09-10 | 1985-04-30 | United Technologies Corporation | Peened overlay coatings |
CA1212020A (en) * | 1981-09-14 | 1986-09-30 | David N. Duhl | Minor element additions to single crystals for improved oxidation resistance |
US4451299A (en) * | 1982-09-22 | 1984-05-29 | United Technologies Corporation | High temperature coatings by surface melting |
US5035958A (en) * | 1983-12-27 | 1991-07-30 | General Electric Company | Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superaloys |
US5043138A (en) * | 1983-12-27 | 1991-08-27 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
GB2152082A (en) * | 1983-12-27 | 1985-07-31 | United Technologies Corp | Enhancement of superalloy resistance to environmental degradation |
US4677035A (en) * | 1984-12-06 | 1987-06-30 | Avco Corp. | High strength nickel base single crystal alloys |
US4711665A (en) * | 1985-07-26 | 1987-12-08 | Pennsylvania Research Corporation | Oxidation resistant alloy |
US4889589A (en) * | 1986-06-26 | 1989-12-26 | United Technologies Corporation | Gaseous removal of ceramic coatings |
US4729799A (en) * | 1986-06-30 | 1988-03-08 | United Technologies Corporation | Stress relief of single crystal superalloy articles |
US4937042A (en) * | 1986-11-28 | 1990-06-26 | General Electric Company | Method for making an abradable article |
US4842953A (en) * | 1986-11-28 | 1989-06-27 | General Electric Company | Abradable article, and powder and method for making |
US5277936A (en) * | 1987-11-19 | 1994-01-11 | United Technologies Corporation | Oxide containing MCrAlY-type overlay coatings |
US4758480A (en) * | 1987-12-22 | 1988-07-19 | United Technologies Corporation | Substrate tailored coatings |
US4851300A (en) * | 1988-05-09 | 1989-07-25 | United Technologies Corporation | Precoat for improving platinum thin film adhesion |
US4916022A (en) * | 1988-11-03 | 1990-04-10 | Allied-Signal Inc. | Titania doped ceramic thermal barrier coatings |
US5015502A (en) * | 1988-11-03 | 1991-05-14 | Allied-Signal Inc. | Ceramic thermal barrier coating with alumina interlayer |
US4944858A (en) * | 1988-12-08 | 1990-07-31 | United Technologies Corporation | Method for applying diffusion aluminide coating |
US5039477A (en) * | 1989-06-02 | 1991-08-13 | Sugitani Kinzoku Kogyo Kabushiki Kaisha | Powdered metal spray coating material |
DE3926479A1 (en) * | 1989-08-10 | 1991-02-14 | Siemens Ag | RHENIUM-PROTECTIVE COATING, WITH GREAT CORROSION AND / OR OXIDATION RESISTANCE |
US5273712A (en) * | 1989-08-10 | 1993-12-28 | Siemens Aktiengesellschaft | Highly corrosion and/or oxidation-resistant protective coating containing rhenium |
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 |
KR930002869B1 (en) * | 1990-12-31 | 1993-04-12 | 포항종합제철 주식회사 | Heat-resisting tube for annealing furnace and process for making |
WO1993013245A1 (en) * | 1991-12-24 | 1993-07-08 | Detroit Diesel Corporation | Thermal barrier coating and method of depositing the same on combustion chamber component surfaces |
US6333121B1 (en) * | 1992-10-13 | 2001-12-25 | General Electric Company | Low-sulfur article having a platinum-aluminide protective layer and its preparation |
US5538796A (en) * | 1992-10-13 | 1996-07-23 | General Electric Company | Thermal barrier coating system having no bond coat |
US5455119A (en) * | 1993-11-08 | 1995-10-03 | Praxair S.T. Technology, Inc. | Coating composition having good corrosion and oxidation resistance |
US5783318A (en) * | 1994-06-22 | 1998-07-21 | United Technologies Corporation | Repaired nickel based superalloy |
CN1068387C (en) * | 1994-06-24 | 2001-07-11 | 普拉塞尔·S·T·技术有限公司 | A process for producing an oxide dispersed mcraly-based coating |
US5716720A (en) * | 1995-03-21 | 1998-02-10 | Howmet Corporation | Thermal barrier coating system with intermediate phase bondcoat |
EP0780484B1 (en) | 1995-12-22 | 2001-09-26 | General Electric Company | Thermal barrier coated articles and method for coating |
US5824423A (en) * | 1996-02-07 | 1998-10-20 | N.V. Interturbine | Thermal barrier coating system and methods |
US5987882A (en) * | 1996-04-19 | 1999-11-23 | Engelhard Corporation | System for reduction of harmful exhaust emissions from diesel engines |
US6422008B2 (en) | 1996-04-19 | 2002-07-23 | Engelhard Corporation | System for reduction of harmful exhaust emissions from diesel engines |
UA32758C2 (en) * | 1998-03-23 | 2002-04-15 | Юнайтед Технолоджіз Корпорейшн Пратт Енд Уітні | METHOD OF ELECTRONIC BEAM OBTAINING OF COATINGS, FREE FROM LEADERS |
US6306515B1 (en) * | 1998-08-12 | 2001-10-23 | Siemens Westinghouse Power Corporation | Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating layers |
EP1094131B1 (en) * | 1999-10-23 | 2004-05-06 | ROLLS-ROYCE plc | A corrosion protective coating for a metallic article and a method of applying a corrosion protective coating to a metallic article |
US6365236B1 (en) | 1999-12-20 | 2002-04-02 | United Technologies Corporation | Method for producing ceramic coatings containing layered porosity |
US6607789B1 (en) | 2001-04-26 | 2003-08-19 | General Electric Company | Plasma sprayed thermal bond coat system |
US6655369B2 (en) | 2001-08-01 | 2003-12-02 | Diesel Engine Transformations Llc | Catalytic combustion surfaces and method for creating catalytic combustion surfaces |
JP2003147464A (en) | 2001-11-02 | 2003-05-21 | Tocalo Co Ltd | Member with high-temperature strength |
WO2004016819A1 (en) * | 2002-08-16 | 2004-02-26 | Alstom Technology Ltd | Intermetallic material and use of said material |
JP4173762B2 (en) * | 2003-04-04 | 2008-10-29 | 株式会社神戸製鋼所 | Method for producing alumina film mainly composed of α-type crystal structure and method for producing laminated film-coated member |
US6769878B1 (en) * | 2003-05-09 | 2004-08-03 | Power Systems Mfg. Llc | Turbine blade airfoil |
EP1541713A1 (en) * | 2003-12-11 | 2005-06-15 | Siemens Aktiengesellschaft | Metallic Protective Coating |
EP1780294A1 (en) * | 2005-10-25 | 2007-05-02 | Siemens Aktiengesellschaft | Alloy, protective coating for protecting a structural member against corrosion and oxidation at high temperatures and structural member |
EP1783236A1 (en) * | 2005-11-04 | 2007-05-09 | Siemens Aktiengesellschaft | Alloy, protecting coating for a component protection against corrosion and oxidation at high temperature and component |
CA2635481C (en) | 2005-12-28 | 2013-08-13 | Ansaldo Energia S.P.A. | Alloy composition for the manufacture of protective coatings, its use, process for its application and super-alloy articles coated with the same composition |
US20070207328A1 (en) * | 2006-03-01 | 2007-09-06 | United Technologies Corporation | High density thermal barrier coating |
US20070248457A1 (en) * | 2006-04-25 | 2007-10-25 | General Electric Company | Rub coating for gas turbine engine compressors |
EP1925687A1 (en) * | 2006-11-24 | 2008-05-28 | Siemens Aktiengesellschaft | NICoCrAl-layer and metallic layer system |
US7879459B2 (en) * | 2007-06-27 | 2011-02-01 | United Technologies Corporation | Metallic alloy composition and protective coating |
US8039117B2 (en) * | 2007-09-14 | 2011-10-18 | Siemens Energy, Inc. | Combustion turbine component having rare earth NiCoCrAl coating and associated methods |
US8043717B2 (en) * | 2007-09-14 | 2011-10-25 | Siemens Energy, Inc. | Combustion turbine component having rare earth CoNiCrAl coating and associated methods |
US8043718B2 (en) * | 2007-09-14 | 2011-10-25 | Siemens Energy, Inc. | Combustion turbine component having rare earth NiCrAl coating and associated methods |
US7867626B2 (en) * | 2007-09-14 | 2011-01-11 | Siemens Energy, Inc. | Combustion turbine component having rare earth FeCrAI coating and associated methods |
DE102007048484A1 (en) | 2007-10-09 | 2009-04-16 | Man Turbo Ag | Hot gas-guided component of a turbomachine |
US20100068405A1 (en) * | 2008-09-15 | 2010-03-18 | Shinde Sachin R | Method of forming metallic carbide based wear resistant coating on a combustion turbine component |
EP2216421A1 (en) * | 2009-01-29 | 2010-08-11 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
WO2011042052A1 (en) * | 2009-10-07 | 2011-04-14 | Siemens Aktiengesellschaft | Component with a substrate and a protective layer |
US20210292910A1 (en) * | 2010-02-26 | 2021-09-23 | Friedhelm Schmitz | Two layered metallic bondcoat |
US20130157078A1 (en) * | 2011-12-19 | 2013-06-20 | General Electric Company | Nickel-Cobalt-Based Alloy And Bond Coat And Bond Coated Articles Incorporating The Same |
US20130323066A1 (en) * | 2012-05-31 | 2013-12-05 | Monika D. Kinstler | Maskant for fluoride ion cleaning |
JP6542750B2 (en) * | 2013-03-13 | 2019-07-10 | ゼネラル・エレクトリック・カンパニイ | Coating of metal substrate |
DE102013209189A1 (en) * | 2013-05-17 | 2014-11-20 | Siemens Aktiengesellschaft | Protective coating and gas turbine component with the protective coating |
EP3071732B1 (en) * | 2013-11-19 | 2019-11-13 | United Technologies Corporation | Article having variable composition coating |
CN111560584A (en) * | 2020-05-22 | 2020-08-21 | 江苏大学 | High-performance thermal barrier coating of aero-engine blade and multi-process combined preparation method |
CN114807823B (en) * | 2022-04-13 | 2023-04-07 | 四川大学 | Preparation method of high-temperature protective coating for hot-end component of gas turbine |
US20240052499A1 (en) | 2022-08-09 | 2024-02-15 | Zhihong Tang | High performance alumina-forming multi- element materials for high temperature applications |
CN115747795B (en) * | 2022-12-05 | 2024-03-26 | 江苏大学 | Thermal barrier coating bonding layer with high service life and preparation method thereof |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB734210A (en) * | 1952-12-09 | 1955-07-27 | Rolls Royce | Improvements relating to processes of manufacturing turbine blades from heat-resisting alloys |
US3754902A (en) * | 1968-06-05 | 1973-08-28 | United Aircraft Corp | Nickel base superalloy resistant to oxidation erosion |
US3649225A (en) * | 1969-11-17 | 1972-03-14 | United Aircraft Corp | Composite coating for the superalloys |
US3754903A (en) * | 1970-09-15 | 1973-08-28 | United Aircraft Corp | High temperature oxidation resistant coating alloy |
US3676085A (en) * | 1971-02-18 | 1972-07-11 | United Aircraft Corp | Cobalt base coating for the superalloys |
-
1974
- 1974-05-13 US US469186A patent/US3928026A/en not_active Expired - Lifetime
-
1975
- 1975-02-24 CA CA220,942A patent/CA1045421A/en not_active Expired
- 1975-04-19 CH CH498775A patent/CH606454A5/xx not_active IP Right Cessation
- 1975-04-28 IL IL47181A patent/IL47181A/en unknown
- 1975-05-06 DE DE2520192A patent/DE2520192C2/en not_active Expired
- 1975-05-07 JP JP50055366A patent/JPS5919977B2/en not_active Expired
- 1975-05-07 SE SE7505339A patent/SE410476B/en not_active IP Right Cessation
- 1975-05-07 FR FR7514277A patent/FR2271299B1/fr not_active Expired
- 1975-05-13 IT IT23242/75A patent/IT1038126B/en active
- 1975-05-13 GB GB20193/75A patent/GB1489796A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
SE7505339L (en) | 1975-11-14 |
DE2520192C2 (en) | 1986-02-06 |
SE410476B (en) | 1979-10-15 |
FR2271299B1 (en) | 1978-06-09 |
FR2271299A1 (en) | 1975-12-12 |
CH606454A5 (en) | 1978-10-31 |
JPS50158531A (en) | 1975-12-22 |
IL47181A0 (en) | 1975-08-31 |
IT1038126B (en) | 1979-11-20 |
CA1045421A (en) | 1979-01-02 |
GB1489796A (en) | 1977-10-26 |
DE2520192A1 (en) | 1975-11-27 |
JPS5919977B2 (en) | 1984-05-10 |
US3928026A (en) | 1975-12-23 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
IL47181A (en) | High temperature nicocraiy coatings | |
US3676085A (en) | Cobalt base coating for the superalloys | |
US4313760A (en) | Superalloy coating composition | |
US4339509A (en) | Superalloy coating composition with oxidation and/or sulfidation resistance | |
US4447503A (en) | Superalloy coating composition with high temperature oxidation resistance | |
US4451431A (en) | Molybdenum-containing high temperature coatings for nickel- and cobalt-based superalloys | |
US4933239A (en) | Aluminide coating for superalloys | |
US6153313A (en) | Nickel aluminide coating and coating systems formed therewith | |
US4714624A (en) | High temperature oxidation/corrosion resistant coatings | |
US5498484A (en) | Thermal barrier coating system with hardenable bond coat | |
US5238752A (en) | Thermal barrier coating system with intermetallic overlay bond coat | |
US3542530A (en) | Nickel or cobalt base with a coating containing iron chromium and aluminum | |
US5316866A (en) | Strengthened protective coatings for superalloys | |
US4145481A (en) | Process for producing elevated temperature corrosion resistant metal articles | |
US5077141A (en) | High strength nickel base single crystal alloys having enhanced solid solution strength and methods for making same | |
US5273712A (en) | Highly corrosion and/or oxidation-resistant protective coating containing rhenium | |
US5035958A (en) | Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superaloys | |
US4885216A (en) | High strength nickel base single crystal alloys | |
US4615864A (en) | Superalloy coating composition with oxidation and/or sulfidation resistance | |
EP0194391B1 (en) | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys | |
US5268238A (en) | Highly corrosion and/or oxidation-resistant protective coating containing rhenium applied to gas turbine component surface and method thereof | |
JP2017053022A (en) | High temperature protective coating | |
JPH02503576A (en) | Coated near-α titanium product | |
EP0358685B1 (en) | Coated near -alpha titanium articles | |
EP0194392B1 (en) | Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superalloys |