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Coating system for superalloys

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US3873347A
US3873347A US34691973A US3873347A US 3873347 A US3873347 A US 3873347A US 34691973 A US34691973 A US 34691973A US 3873347 A US3873347 A US 3873347A
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coating
coated
nickel
aluminum
body
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James L Walker
John R Ross
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General Electric Co
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General Electric Co
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    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C14/00Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14Metallic material, boron or silicon
    • C23C14/16Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C10/00Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02Pretreatment of the material to be coated
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C28/00Coating 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
    • C23C28/02Coating 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
    • C23C28/021Coating 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
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C28/00Coating 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
    • C23C28/02Coating 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
    • C23C28/023Coating 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
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S428/00Stock material or miscellaneous articles
    • Y10S428/922Static electricity metal bleed-off metallic stock
    • Y10S428/923Physical dimension
    • Y10S428/924Composite
    • Y10S428/926Thickness of individual layer specified
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/12All metal or with adjacent metals
    • Y10T428/12493Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736Al-base component
    • Y10T428/1275Next to Group VIII or IB metal-base component
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/12All metal or with adjacent metals
    • Y10T428/12493Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736Al-base component
    • Y10T428/1275Next to Group VIII or IB metal-base component
    • Y10T428/12757Fe
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/12All metal or with adjacent metals
    • Y10T428/12493Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771Transition metal-base component
    • Y10T428/12861Group VIII or IB metal-base component
    • Y10T428/12931Co-, Fe-, or Ni-base components, alternative to each other

Abstract

A protective coating system is provided for nickel-base and cobalt-base superalloys which is capable of imparting oxidation and corrosion resistance at elevated temperatures. 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.

Description

1451 Mar. 25, 1975 COATING SYSTEM FOR SUPERALLOYS Inventors: James L. Walker; John R. Ross,

both of Schenectady, N.Y.

Assignee: General Electric Company,

Schenectady, NY.

Filed: Apr. 2, 1973 Appl. No.: 346,919

11.8. Cl. 117/71 M, l17/107.2 P Int. Cl. B44d l/16 Field of Search ll7/7l M, 107, 107.2 P

References Cited UNITED STATES PATENTS 7/1971 Maxwell et al 117/107.2 P 2/1972 Schwartz et a1. 117/107.2 P 7/1972 Evans ct al. 117/107 Primary Examiner-Cameron K. Weiffenbach Attorney, Agent, or Firm--Gerhard K. Adam; Joseph T. Cohen; Jerome C. Squillaro [5 7] ABSTRACT A protective coating system is provided for nickelbase and cobalt-base superalloys which is capable of imparting oxidation and corrosion resistance at ele' vated temperatures. 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.

8 Claims, 5 Drawing Figures COATING SYSTEM FOR SUPERALLOYS 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.

Heretofore, surface coatings have been used to protect the superalloy articles from high temperature oxidation and corrosion. Various coatings for superalloys have been described in the literature and of particular interest are 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. During this procedure, 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. Unfortunately, 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.

Attempts to prolong the useful life of superalloys coated with a FeCrAlY alloy are disclosed by Elam, et al., US. Pat. No. 3,528,861. The coating effectiveness was found to be limited by the formation of an intergranular precipitate during the coating deposition cycle. The effect of the detrimental precipitate was improved by shot peening or glass bead blasting to bteak up the precipitate into small particles which are more easily taken into solution by heat treatment.

In accordance with the present invention, we have invented 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. Upon exposure to a corrosive environment, these boundaries are preferentially attacked resulting in ultimate failure of the coating. The application of an aluminizing overcoat prevents this type of failure and thereby substantially increases the life of the coated article. In addition, 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.

The invention is more clearly understood from the following description taken in conjunction with the accompanying drawing in which:

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:

Ingredients Weight Chromium 14 -35 Aluminum 4 20 Yttrium 0.1- 3 Iron Cobalt Balance Nickel Included in this formulation are the compositions designated hereinabove as FeCrAlY, CoCrAlY, and Ni- CrAlY. 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. During evaporation, 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. During coating 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.

Thereafter, 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. In a preferred embodiment, 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. In a specific embodiment as disclosed by Levine, et al., 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. 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. During preparation of such a mixture, 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. Upon application of the aluminizing overcoat, 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.

Our invention is further illustrated by the following examples.

EXAMPLE I Ingredient Weight Cobalt 64 Chromium 22 Aluminum l 3 Yttrium I Evaporation of the metal was at a constant power of 19.0 kilovolts and 275 milliamps for 30 minutes. The pins were then cooled in vacuum. A coating having a thickness of about 3 mils was deposited on the pins.

One group of coated pins was then lightly sand blasted to prepare the surface for vapor deposition. 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.

It was observed that the samples coated only with the CoCrAlY coating were characterized by deep spike" corrosion, but the pins subjected to the aluminizing overcoating procedure were substantially more resistant to attack by corrosion.

EXAMPLE II Following the procedure of Example I, 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:

After the pins were removed from the apparatus, the coating had a thickness of 3-5 mils.

Thereafter the 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. In the crucible test, 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. The results indicated almost a complete absence of spike corrosion and that the aluminized coating had filled in the defects of the initial coating.

Another group of samples was subjected to a burner rig test which simulated conditions used in a gas turbine engine. The test was run of 2,000 hours at a temperature of l,475 F. using a jet fuel containing 1 ppm. sea salt and 5 ppm. of vanadium pentoxide. The results indicated that CoCrAlY coated samples were heavily attacked whereas the aluminized overcoated samples were still intact.

EXAMPLE III Following the procedure of Example I, cast pins of Rene 80 nickel-base superalloy were coated by vapor deposition with the following nominal composition:

b Ingredient Weight Nickel 6 l .5 Cobalt 9.5 Chromium 25.0 Aluminum 3.0 Yttrium 1.0

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.

When subjected to the corrosion tests it was observed that the pins subjected to the aluminizing overcoat procedure were considerably more resistant to corrosion than those which had been coated only with the MCrAlY coating.

It will be appreciated that the invention is not limited to the specific details ssown in the examples and illustrations and that various modifications may be made within the ordinary skill in the art without departing from the spirit and scope of the invention.

We claim: I

l. 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:

a. 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 b. subjecting the coated body to an aluminizing overcoating by pack cementation to increase the oxidation and corrosion resistance of the coating.

2. The method of claim 1, wherein said 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.

3. The method of claim 1, wherein said composition consists essentially in weight percent of 25-29% chromium, 12-14% aluminum, 06-09% yttrium and the balance being iron.

4. The method of claim ll, wherein said composition consists essentially in weight percent of 19-24% chromium, 13-17% aluminum, 06-09% yttrium, and the balance being cobalt.

5. The method of claim 1, wherein said composition consists essentially in weight percent of 20-35% chromium, 15-20% aluminum, 0.050.30% yttrium and the balance being nickel.

6. The method of claim 1, wherein said body is a nickel-base superalloy.

7. The method of claim 1, wherein said body is a cobalt-base superalloy.

8. The method of claim 1, wherein the first coating has a thickness of about 3-5 mils and the aluminizing overcoating penetrates into the first coating to a depth of about l-2 mils.

Claims (8)

1. 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: A. 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 B. SUBJECTING THE COATED BODY TO AN ALUMINIZING OVERCOATING BY PACK CEMENTATION TO INCREASE THE OXIDATION AND CORROSION RESISTANCE OF THE COATING.
2. The method of claim 1, wherein said composition consists essentially in weight percent of 14-35% chromium, 4-20% aluminum, 0.1-3% yttrium and the balance being a member selected from the group consisting of iron, cobalt, nickel, and mixtures thereof.
3. The method of claim 1, wherein said composition consists essentially in weight percent of 25-29% chromium, 12-14% aluminum, 0.6-0.9% yttrium and the balance being iron.
4. The method of claim 1, wherein said composition consists essentially in weight percent of 19-24% chromium, 13-17% aluminum, 0.6-0.9% yttrium, and the balance being cobalt.
5. The method of claim 1, wherein said composition consists essentially in weight percent of 20-35% chromium, 15-20% aluminum, 0.05-0.30% yttrium and the balance being nickel.
6. The method of claim 1, wherein said body is a nickel-base superalloy.
7. The method of claim 1, wherein said body is a cobalt-base superalloy.
8. The method of claim 1, wherein the first coating has a thickness of about 3-5 mils and the aluminizing overcoating penetrates into the first coating to a depth of about 1-2 mils.
US3873347A 1973-04-02 1973-04-02 Coating system for superalloys Expired - Lifetime US3873347A (en)

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US3873347A US3873347A (en) 1973-04-02 1973-04-02 Coating system for superalloys
NL7400369A NL7400369A (en) 1973-04-02 1974-01-10
DE19742414992 DE2414992A1 (en) 1973-04-02 1974-03-28 Ueberzugssystem for super alloys
GB1401374A GB1460317A (en) 1973-04-02 1974-03-29 Coating systems for superalloys
BE142684A BE813097A (en) 1973-04-02 1974-03-29 Process for coating of elements in super-alloy and obtained Elements
FR7411192A FR2223478B1 (en) 1973-04-02 1974-03-29
JP3570974A JPS5029436A (en) 1973-04-02 1974-04-01
US05508747 US4080486A (en) 1973-04-02 1974-09-24 Coating system for superalloys

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Cited By (46)

* Cited by examiner, † Cited by third party
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
US4123595A (en) * 1977-09-22 1978-10-31 General Electric Company Metallic coated article
US4123594A (en) * 1977-09-22 1978-10-31 General Electric Company Metallic coated article of improved environmental resistance
US4145481A (en) * 1977-08-03 1979-03-20 Howmet Turbine Components Corporation Process for producing elevated temperature corrosion resistant metal articles
DE2820289A1 (en) * 1978-05-10 1979-11-15 Leybold Heraeus Gmbh & Co Kg A process for coating metallic substrates with alloy layers at an elevated substrate temperature
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
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US4407871A (en) * 1980-03-25 1983-10-04 Ex-Cell-O Corporation Vacuum metallized dielectric substrates and method of making same
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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
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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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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
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US6634860B2 (en) * 2001-12-20 2003-10-21 General Electric Company Foil formed structure for turbine airfoil tip
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
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
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
US20090075111A1 (en) * 2007-09-14 2009-03-19 Siemens Power Generation, Inc. Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods
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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US8043717B2 (en) 2007-09-14 2011-10-25 Siemens Energy, Inc. Combustion turbine component having rare earth CoNiCrAl coating and associated methods
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RU2574542C1 (en) * 2015-03-20 2016-02-10 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Production of reinforcing sandwiched coatings

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GB1460317A (en) 1977-01-06 application
FR2223478A1 (en) 1974-10-25 application
BE813097A1 (en) grant
BE813097A (en) 1974-07-15 grant
NL7400369A (en) 1974-10-04 application
DE2414992A1 (en) 1974-10-03 application
US4080486A (en) 1978-03-21 grant
FR2223478B1 (en) 1978-11-17 grant
JPS5029436A (en) 1975-03-25 application

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