US3873347A - Coating system for superalloys - Google Patents
Coating system for superalloys Download PDFInfo
- Publication number
- US3873347A US3873347A US346919A US34691973A US3873347A US 3873347 A US3873347 A US 3873347A US 346919 A US346919 A US 346919A US 34691973 A US34691973 A US 34691973A US 3873347 A US3873347 A US 3873347A
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- US
- United States
- Prior art keywords
- coating
- nickel
- cobalt
- aluminum
- chromium
- 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 - Lifetime
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Classifications
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- 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
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/02—Pretreatment of the material to be coated
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- 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
- C23C28/02—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 only coatings only including layers of metallic material
- C23C28/021—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 only coatings only including layers of metallic material including at least one metal alloy layer
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- 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
- C23C28/02—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 only coatings only including layers of metallic material
- C23C28/023—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 only coatings only including layers of metallic material only coatings of metal elements only
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- 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.]
- Y10T428/12736—Al-base component
- Y10T428/1275—Next to 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.]
- Y10T428/12736—Al-base component
- Y10T428/1275—Next to Group VIII or IB metal-base component
- Y10T428/12757—Fe
-
- 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
Definitions
- the superalloy body is first coated by physical vapor deposition with a composition consisting essentially of chromium, aluminum, a member selected from the group consisting of yttrium and the rare earth elements, and at least one element selected from the group consisting of iron, cobalt and nickel, and thereafter the body is subjected to an aluminizing overcoating to increase the corrosion resistance.
- the superalloys are heat-resistant materials having superior strengths at high temperatures. Many of these alloys contain iron, nickel or cobalt alone or in combination as the principal alloying elements together with chromium to impart surface stability and usually contain one or more minor constituents, such as molybdenum, tungsten, columbium, titanium and aluminum for the purpose of effecting strengthening. The physical properties of the superalloys make them particularly useful in the manufacture of gas turbine engine components.
- coating compositions consisting essentially of chromium, aluminum, a member selected from the group consisting of yttrium and the rare earth elements and a metal selected from the group consisting of iron, cobalt, and nickel.
- Illustrative coatings wherein the compositions are given in weight percent are designated as follows:
- the application of the coating composition to a variety of substrates, such as nickel-base and cobalt-base superalloys may be achieved by physical vapor deposition in a vacuum chamber.
- the composition is thermally evaporated from a source heated, for example, by an electron beam, and a thin metal coating is condensed on the surface of the workpiece. Layers of the coating are formed as the workpiece is rotated until the thickness is in the range of about 3-5 mils.
- the deposited coating has radially oriented defects which are the sites of attack by oxidizing and/or corrosive atmospheres at high temperatures. Such defects can lead to premature failure of the coating.
- a method of improving the high temperature corrosion resistance of a nickel-base or cobalt-base superalloy body by first coating the superalloy body by physical vapor deposition with a composition consisting essentially of chromium, aluminum, a member selected from the group consisting of yttrium and the rare earth elements, and at least one element selected from the group consisting of iron, cobalt and nickel and thereafter aluminizing the coated body by chemical vapor deposition to increase the corrosion resistance of the body.
- the effectiveness of the coating system may be explained by the fact that the first coating exhibits grain boundaries that are oriented in a perpendicular direction to the deposition plane.
- the concentration profile of our novel coating system indicates the presence of a high concentration of aluminum on the outer surface of the coating which may also contribute to the improved properties.
- the coated superalloy bodies prepared by our invention are particularly useful in making gas turbine engine components.
- FIG. 1 is a photomicrograph 500x of a Rene 8O nickel-base superalloy body coated with a Ni- CrAlY coating.
- FIG. 2 is a photomicrograph (500 of a Rene nickel-base superalloy body coated with a first Ni- CrAlY coating and then treated with an aluminizing overcoat according to the method of our invention.
- FIG. 3 is a photomicrograph (SOOX) illustrating the effect of corrosion on a CoCrAlY coated superalloy body.
- FIG. 4 is a photomicrograph (500 illustrating the effect of corrosion on a superalloy body coated first with a CoCrAlY coating and then treated with an aluminizing overcoat.
- FIG. 5 is a microprobe profile of a body prepared by our invention and showing the high surface gradient of aluminum.
- the superalloys are strong, high temperature materials which are particularly useful in gas turbine engines. A substantial listing of these materials is set forth by W. F. Simmons, Compilation of Chemical Compositions and Rupture Strengths 0f Superalloys, ASTM Data Series Publication No. DS9E, and may be represented by the nominal compositions in weight percent of the following superalloys:
- the first coating of our protective coating system is designated herein as MCrAlY" coating wherein M is a member selected from the group consisting of iron, cobalt, and nickel.
- This coating is broadly defined as consisting essentially in weight percent of the following nominal compositions:
- the MCrAlY coating is applied to the substrate by a physical vapor deposition technique which is described in considerable detail in Vapor Deposition, Edited by C. F. Powell, et al., John Wiley & Sons, New York (1966). Accordingly, the coating is evaporated and deposited in a vacuum chamber. Typically, the metal alloy is heated by an electron beam focused on the metal alloy ingot to evaporate the metal to a vapor.
- the vapor condenses as a coating, preferably about 3-5 mils in thickness on the workpiece being coated.
- the material to be applied is heated in a high vacuum to a temperature at which its vapor pressure is about l"torr or greater whereupon it emits molecular rays in all directions.
- the vacuum must be very high to permit the molecular rays to travel from their source without disturbance until they hit the surface of the object to be coated.
- a photomicrograph of a nickel-base superalloy coated with a NiCrAlY coating is shown in FIG. 1.
- the first coating is treated by an aluminizing overcoat by a chemical vapor deposition technique such as illustrated by Levine, et al., U.S. Pat. No. 3,540,878, and as discussed in Powell, et al., cited hereinabove.
- the aluminizing is performed by a pack-cementation method in which the article is packed in a porous mixture of refractory particles and granular aluminum or an aluminum containing alloy and heated to between 600-l ,000 C. in the presence of a halide salt activator.
- the particulate pack mixture includes a powder of a multiphase ternary alloy of Ti, Al and C, an inert filler which will not react with the other components of the mixture to prevent powder sintering, and a halide salt activator such as member selected from the chlorides and fluorides of ammonia and the alkali 'metals.
- a halide salt activator such as member selected from the chlorides and fluorides of ammonia and the alkali 'metals.
- the most practical activator is a halide salt selected from NaF, KF, NH C1 and NI-I F in an amount of about 01-10 percent by weight of the mixture.
- the preferred filler material is refractory alumina powder which comprises about -985 weight percent of the total pack powder.
- the filler powder, the powdered ternary alloy and the activator are blended together in a conventional mixing apparatus such as an ordinary powder blender.
- An illustrative pack contains about 4 percent by weight of the ternary alloy of Ti, Al and C.
- a photomicrograph of a nickel-base superalloy which has been coated with a first coating of a NiCr- AIY alloy and then an aluminizing overcoating is shown in FIG. 2.
- the first coating exhibited grain boundaries that are oriented in a perpendicular direction to the deposition plane, which become sites for attack by high temperature oxidation and corrosion.
- any open defects of an MCrAlY coating become filled and a high concentration of aluminum is deposited on the outer surface of the coating as shown in FIG. 5 (a concentration profile of a CoCrAlY coated Rene 80 body with an aluminizing overcoating). It is to this unique coating system that we attribute the improved properties of high temperature oxidation and corrosion resistance.
- the aluminizing mixture was prepared by mixing 30 g. of+200-350 mesh NiAl powder and 270 g. of alumina in a suitable container. Then 300 ml. ofa 0.2% aqueous NH F solution was added and the contents heated to about 300 C., while mixing occasionally to remove the water by evaporation.
- the completely dry powder was put into an Inconel metal box (with two holes in the top of each end) in an amount of at least 3 g. of powder to each square centimeter of surface to be aluminized.
- the CoCrAlY coated samples were put in the box and completely covered by the powder.
- the box was then covered and placed in a retort that had approximately 0.5 cu. ft./hr. of hydrogen flowing through it and placed in a furnace.
- the furnace was heated to 850 C., held at that temperature for 1 hour and then cooled to room temperature. Upon examination of the sample it was noted that this procedure resulted in a penetration of about l-2 mils of aluminum into the surface of the CoCrAlY coating.
- a crucible test was then performed to test resistance to oxidation and corrosion of the samples coated only with the CoCrAlY coating and the second group subjected to a subsequent aluminizing procedure. Both groups of coated pins were immersed in a bath of Na SO V O (%:25% by weight) at a temperature of 900 C., while gaseous oxygen was bubbled through the bath. After 18 hours the samples were removed.
- test pins having a diameter of one-eighth in. were prepared from Rene 80 nickel-base superalloy.
- the pins were coated by electron beam evaporation with the following nominal composition:
- the coating had a thickness of 3-5 mils.
- coated pins were aluminized by the pack cementation technique.
- a pack composition was prepared to meet the following specification in weight percent: 60% Ti, 33.5% Al, and 4.8-5.6% C.
- a 1 V2 percent by weight pack was prepared by diluting the pack in 98.5% by weight of A1
- the coated pins were then embedded in the powder mixture and aluminized at a temperature of l,925 F. for 4 hours.
- Comparative high temperature oxidation and corrosion tests were performed on test samples coated only with the CoCrAlY alloy and on test samples which had been subsequently subjected to the aluminizing overcoat.
- the pins were partially immersed in sodium sulfate and a mixture of 80 parts by weight of sodium sulfate and 20 parts by weight of vanadium pentoxide for a time of 16 hours.
- the samples coated only with the CoCrAlY coating after being subjected to a temperature of l,925 F. for 1 hour in vacuum are shown in FIG. 3.
- Typical spike corrosion and penetration were observed.
- the samples which had been protected by the aluminizing overcoat, after being subjected to a temperature of 1,925 F. for 4 hours in vacuum are shown in FIG. 4.
- a coating having a thickness of about 3 mils was deposited on the pins. Some of the pins were then aluminized by the pack cementation technique described in Example I.
- a method of improving the high temperature oxidation and corrosion resistance of a nickel-base or a cobalt-base superalloy body comprising the steps of:
- composition consists essentially in weight percent of 14-35% chromium, 4-20% aluminum, 0.l-3% yttrium and the balance being a member selected from the group consisting of iron, cobalt, nickel, and mixtures thereof.
- composition consists essentially in weight percent of 25-29% chromium, 12-14% aluminum, 06-09% yttrium and the balance being iron.
- composition consists essentially in weight percent of 19-24% chromium, 13-17% aluminum, 06-09% yttrium, and the balance being cobalt.
- composition consists essentially in weight percent of 20-35% chromium, 15-20% aluminum, 0.050.30% yttrium and the balance being nickel.
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- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physical Vapour Deposition (AREA)
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Priority Applications (11)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US346919A US3873347A (en) | 1973-04-02 | 1973-04-02 | Coating system for superalloys |
IL43899A IL43899A0 (en) | 1973-04-02 | 1973-12-23 | Coating system for superalloys |
NL7400369A NL7400369A (ja) | 1973-04-02 | 1974-01-10 | |
DE2414992A DE2414992A1 (de) | 1973-04-02 | 1974-03-28 | Ueberzugssystem fuer superlegierungen |
BE142684A BE813097A (fr) | 1973-04-02 | 1974-03-29 | Procede de revetement d'elements en super-alliage et elements obtenus |
IT49855/74A IT1005893B (it) | 1973-04-02 | 1974-03-29 | Sistema di rivestimento per super leghe |
FR7411192A FR2223478B1 (ja) | 1973-04-02 | 1974-03-29 | |
GB1401374A GB1460317A (en) | 1973-04-02 | 1974-03-29 | Coating systems for superalloys |
JP49035709A JPS5029436A (ja) | 1973-04-02 | 1974-04-01 | |
NO741155A NO741155L (no) | 1973-04-02 | 1974-04-01 | Fremgangsmåte ved belegning av en nikkelbasert eller koboltbasert superlegeringsgjenstand |
US05/508,747 US4080486A (en) | 1973-04-02 | 1974-09-24 | Coating system for superalloys |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US346919A US3873347A (en) | 1973-04-02 | 1973-04-02 | Coating system for superalloys |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US05/508,747 Division US4080486A (en) | 1973-04-02 | 1974-09-24 | Coating system for superalloys |
Publications (1)
Publication Number | Publication Date |
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US3873347A true US3873347A (en) | 1975-03-25 |
Family
ID=23361584
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US346919A Expired - Lifetime US3873347A (en) | 1973-04-02 | 1973-04-02 | Coating system for superalloys |
US05/508,747 Expired - Lifetime US4080486A (en) | 1973-04-02 | 1974-09-24 | Coating system for superalloys |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US05/508,747 Expired - Lifetime US4080486A (en) | 1973-04-02 | 1974-09-24 | Coating system for superalloys |
Country Status (10)
Country | Link |
---|---|
US (2) | US3873347A (ja) |
JP (1) | JPS5029436A (ja) |
BE (1) | BE813097A (ja) |
DE (1) | DE2414992A1 (ja) |
FR (1) | FR2223478B1 (ja) |
GB (1) | GB1460317A (ja) |
IL (1) | IL43899A0 (ja) |
IT (1) | IT1005893B (ja) |
NL (1) | NL7400369A (ja) |
NO (1) | NO741155L (ja) |
Cited By (47)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4101713A (en) * | 1977-01-14 | 1978-07-18 | General Electric Company | Flame spray oxidation and corrosion resistant superalloys |
US4117179A (en) * | 1976-11-04 | 1978-09-26 | General Electric Company | Oxidation corrosion resistant superalloys and coatings |
US4123594A (en) * | 1977-09-22 | 1978-10-31 | General Electric Company | Metallic coated article of improved environmental resistance |
US4123595A (en) * | 1977-09-22 | 1978-10-31 | General Electric Company | Metallic coated article |
US4145481A (en) * | 1977-08-03 | 1979-03-20 | Howmet Turbine Components Corporation | Process for producing elevated temperature corrosion resistant metal articles |
DE2820289A1 (de) * | 1978-05-10 | 1979-11-15 | Leybold Heraeus Gmbh & Co Kg | Verfahren zum beschichten von metallischen substraten mit legierungsschichten bei erhoehter substrattemperatur |
US4218007A (en) * | 1979-02-22 | 1980-08-19 | General Electric Company | Method of diffusion bonding duplex sheet cladding to superalloy substrates |
US4237193A (en) * | 1978-06-16 | 1980-12-02 | General Electric Company | Oxidation corrosion resistant superalloys and coatings |
US4246323A (en) * | 1977-07-13 | 1981-01-20 | United Technologies Corporation | Plasma sprayed MCrAlY coating |
US4275090A (en) * | 1978-10-10 | 1981-06-23 | United Technologies Corporation | Process for carbon bearing MCrAlY coating |
US4275124A (en) * | 1978-10-10 | 1981-06-23 | United Technologies Corporation | Carbon bearing MCrAlY coating |
US4326011A (en) * | 1980-02-11 | 1982-04-20 | United Technologies Corporation | Hot corrosion resistant coatings |
USRE30995E (en) * | 1977-06-09 | 1982-07-13 | General Electric Company | High integrity CoCrAl(Y) coated nickel-base superalloys |
US4382976A (en) * | 1979-07-30 | 1983-05-10 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Method of forming corrosion resistant coatings on metal articles |
USRE31339E (en) * | 1977-08-03 | 1983-08-09 | Howmet Turbine Components Corporation | Process for producing elevated temperature corrosion resistant metal articles |
US4401697A (en) * | 1980-01-07 | 1983-08-30 | United Technologies Corporation | Method for producing columnar grain ceramic thermal barrier coatings |
US4405660A (en) * | 1980-01-07 | 1983-09-20 | United Technologies Corporation | Method for producing metallic articles having durable ceramic thermal barrier coatings |
US4405659A (en) * | 1980-01-07 | 1983-09-20 | United Technologies Corporation | Method for producing columnar grain ceramic thermal barrier coatings |
US4407871A (en) * | 1980-03-25 | 1983-10-04 | Ex-Cell-O Corporation | Vacuum metallized dielectric substrates and method of making same |
US4414249A (en) * | 1980-01-07 | 1983-11-08 | United Technologies Corporation | Method for producing metallic articles having durable ceramic thermal barrier coatings |
US4431711A (en) * | 1980-03-25 | 1984-02-14 | Ex-Cell-O Corporation | Vacuum metallizing a dielectric substrate with indium and products thereof |
US4677034A (en) * | 1982-06-11 | 1987-06-30 | General Electric Company | Coated superalloy gas turbine components |
US4897315A (en) * | 1985-10-15 | 1990-01-30 | United Technologies Corporation | Yttrium enriched aluminide coating for superalloys |
US4910092A (en) * | 1986-09-03 | 1990-03-20 | United Technologies Corporation | Yttrium enriched aluminide coating for superalloys |
US4933239A (en) * | 1989-03-06 | 1990-06-12 | United Technologies Corporation | Aluminide coating for superalloys |
USRE33876E (en) * | 1975-09-11 | 1992-04-07 | United Technologies Corporation | Thermal barrier coating for nickel and cobalt base super alloys |
US5366765A (en) * | 1993-05-17 | 1994-11-22 | United Technologies Corporation | Aqueous slurry coating system for aluminide coatings |
US5384200A (en) * | 1991-12-24 | 1995-01-24 | Detroit Diesel Corporation | Thermal barrier coating and method of depositing the same on combustion chamber component surfaces |
US5725905A (en) * | 1993-12-23 | 1998-03-10 | Mtu Motoren- Und Turbinen-Union | Method of manufacturing a component with a protective arrangement which prevents aluminizing or chromizing during gas diffusion coating |
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 |
US6472018B1 (en) | 2000-02-23 | 2002-10-29 | Howmet Research Corporation | Thermal barrier coating method |
US6585864B1 (en) | 2000-06-08 | 2003-07-01 | Surface Engineered Products Corporation | Coating system for high temperature stainless steel |
US6634860B2 (en) * | 2001-12-20 | 2003-10-21 | General Electric Company | Foil formed structure for turbine airfoil tip |
US6635362B2 (en) | 2001-02-16 | 2003-10-21 | Xiaoci Maggie Zheng | High temperature coatings for gas turbines |
US20030200835A1 (en) * | 2002-04-02 | 2003-10-30 | Snecma Services | Diffusion-brazing filler powder for parts made of an alloy based on nickel, cobalt or iron |
US6655369B2 (en) | 2001-08-01 | 2003-12-02 | Diesel Engine Transformations Llc | Catalytic combustion surfaces and method for creating catalytic combustion surfaces |
US6818321B2 (en) | 2001-11-02 | 2004-11-16 | Tocalo Co., Ltd. | High-temperature strength member |
US20060292390A1 (en) * | 2004-07-16 | 2006-12-28 | Mtu Aero Engines Gmbh | Protective coating for application to a substrate and method for manufacturing a protective coating |
US20090075110A1 (en) * | 2007-09-14 | 2009-03-19 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare Earth NiCoCrAl Coating and Associated Methods |
US20090075112A1 (en) * | 2007-09-14 | 2009-03-19 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare Earth FeCrAl Coating and Associated Methods |
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US20100043597A1 (en) * | 2008-08-19 | 2010-02-25 | Arrell Douglas J | Method of making rare-earth strengthened components |
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US4123594A (en) * | 1977-09-22 | 1978-10-31 | General Electric Company | Metallic coated article of improved environmental resistance |
DE2820289A1 (de) * | 1978-05-10 | 1979-11-15 | Leybold Heraeus Gmbh & Co Kg | Verfahren zum beschichten von metallischen substraten mit legierungsschichten bei erhoehter substrattemperatur |
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DE3006103A1 (de) * | 1979-02-22 | 1980-09-04 | Gen Electric | Verfahren zum diffusionsverbinden eines doppelblechueberzuges mit einem substrat aus einer superlegierung |
US4218007A (en) * | 1979-02-22 | 1980-08-19 | General Electric Company | Method of diffusion bonding duplex sheet cladding to superalloy substrates |
US4382976A (en) * | 1979-07-30 | 1983-05-10 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Method of forming corrosion resistant coatings on metal articles |
US4401697A (en) * | 1980-01-07 | 1983-08-30 | United Technologies Corporation | Method for producing columnar grain ceramic thermal barrier coatings |
US4405660A (en) * | 1980-01-07 | 1983-09-20 | United Technologies Corporation | Method for producing metallic articles having durable ceramic thermal barrier coatings |
US4405659A (en) * | 1980-01-07 | 1983-09-20 | United Technologies Corporation | Method for producing columnar grain ceramic thermal barrier coatings |
US4414249A (en) * | 1980-01-07 | 1983-11-08 | United Technologies Corporation | Method for producing metallic articles having durable ceramic thermal barrier coatings |
US4326011A (en) * | 1980-02-11 | 1982-04-20 | United Technologies Corporation | Hot corrosion resistant coatings |
US4407871A (en) * | 1980-03-25 | 1983-10-04 | Ex-Cell-O Corporation | Vacuum metallized dielectric substrates and method of making same |
US4431711A (en) * | 1980-03-25 | 1984-02-14 | Ex-Cell-O Corporation | Vacuum metallizing a dielectric substrate with indium and products thereof |
US4677034A (en) * | 1982-06-11 | 1987-06-30 | General Electric Company | Coated superalloy gas turbine components |
US4897315A (en) * | 1985-10-15 | 1990-01-30 | United Technologies Corporation | Yttrium enriched aluminide coating for superalloys |
US4910092A (en) * | 1986-09-03 | 1990-03-20 | United Technologies Corporation | Yttrium enriched aluminide coating for superalloys |
US4933239A (en) * | 1989-03-06 | 1990-06-12 | United Technologies Corporation | Aluminide coating for superalloys |
US5384200A (en) * | 1991-12-24 | 1995-01-24 | Detroit Diesel Corporation | Thermal barrier coating and method of depositing the same on combustion chamber component surfaces |
US5366765A (en) * | 1993-05-17 | 1994-11-22 | United Technologies Corporation | Aqueous slurry coating system for aluminide coatings |
US5725905A (en) * | 1993-12-23 | 1998-03-10 | Mtu Motoren- Und Turbinen-Union | Method of manufacturing a component with a protective arrangement which prevents aluminizing or chromizing during gas diffusion coating |
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US6472018B1 (en) | 2000-02-23 | 2002-10-29 | Howmet Research Corporation | Thermal barrier coating method |
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US6585864B1 (en) | 2000-06-08 | 2003-07-01 | Surface Engineered Products Corporation | Coating system for high temperature stainless steel |
US6635362B2 (en) | 2001-02-16 | 2003-10-21 | Xiaoci Maggie Zheng | High temperature coatings for gas turbines |
US6655369B2 (en) | 2001-08-01 | 2003-12-02 | Diesel Engine Transformations Llc | Catalytic combustion surfaces and method for creating catalytic combustion surfaces |
US20050016512A1 (en) * | 2001-08-01 | 2005-01-27 | Gillston Lionel M. | Catalytic combustion surfaces and method for creating catalytic combustion surfaces |
US7527048B2 (en) | 2001-08-01 | 2009-05-05 | Diesel Engine Transformation Llc | Catalytic combustion surfaces and method for creating catalytic combustion surfaces |
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US20030200835A1 (en) * | 2002-04-02 | 2003-10-30 | Snecma Services | Diffusion-brazing filler powder for parts made of an alloy based on nickel, cobalt or iron |
US7422769B2 (en) | 2004-07-16 | 2008-09-09 | Mtu Aero Engines Gmbh | Protective coating for application to a substrate and method for manufacturing a protective coating |
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US8039117B2 (en) | 2007-09-14 | 2011-10-18 | Siemens Energy, Inc. | Combustion turbine component having rare earth NiCoCrAl coating and associated methods |
US20090075101A1 (en) * | 2007-09-14 | 2009-03-19 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare Earth CoNiCrAl Coating and Associated Methods |
US20090075111A1 (en) * | 2007-09-14 | 2009-03-19 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods |
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US20090075110A1 (en) * | 2007-09-14 | 2009-03-19 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare Earth NiCoCrAl 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 |
US8043717B2 (en) | 2007-09-14 | 2011-10-25 | Siemens Energy, Inc. | Combustion turbine component having rare earth CoNiCrAl coating and associated methods |
US20100043597A1 (en) * | 2008-08-19 | 2010-02-25 | Arrell Douglas J | Method of making rare-earth strengthened components |
US8029596B2 (en) | 2008-08-19 | 2011-10-04 | Siemens Energy, Inc. | Method of making rare-earth strengthened components |
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 |
RU2574542C1 (ru) * | 2015-03-20 | 2016-02-10 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Способ получения упрочняющих многослойных покрытий |
US11542586B2 (en) * | 2018-08-07 | 2023-01-03 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | Coating for refractory alloy part |
Also Published As
Publication number | Publication date |
---|---|
GB1460317A (en) | 1977-01-06 |
IL43899A0 (en) | 1974-03-14 |
US4080486A (en) | 1978-03-21 |
IT1005893B (it) | 1976-09-30 |
FR2223478A1 (ja) | 1974-10-25 |
NL7400369A (ja) | 1974-10-04 |
BE813097A (fr) | 1974-07-15 |
FR2223478B1 (ja) | 1978-11-17 |
NO741155L (no) | 1974-10-03 |
DE2414992A1 (de) | 1974-10-03 |
JPS5029436A (ja) | 1975-03-25 |
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