US3415672A - Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt - Google Patents

Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt Download PDF

Info

Publication number
US3415672A
US3415672A US410645A US41064564A US3415672A US 3415672 A US3415672 A US 3415672A US 410645 A US410645 A US 410645A US 41064564 A US41064564 A US 41064564A US 3415672 A US3415672 A US 3415672A
Authority
US
United States
Prior art keywords
aluminum
alloy
titanium
binary
nickel
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
Application number
US410645A
Inventor
Moses A Levinstein
John W Grenier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US410645A priority Critical patent/US3415672A/en
Priority to GB42583/65A priority patent/GB1100176A/en
Priority to BE672291D priority patent/BE672291A/xx
Priority to DE19651521269 priority patent/DE1521269C3/en
Application granted granted Critical
Publication of US3415672A publication Critical patent/US3415672A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks
    • 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
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/52—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in one step
    • 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
    • Y10S428/9335—Product by special process
    • Y10S428/938—Vapor deposition or gas diffusion
    • 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
    • Y10T428/12743—Next to refractory [Group IVB, VB, or VIB] 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

Definitions

  • This invention relates to the treatment of metallic surfaces, and more particularly, to the treatment with a binary Ti-Al alloy of metallic surfaces based on alloys of iron, nickel and cobalt.
  • Components of modern power producing apparatus for example turbine components of jet engines, are exposed to temperatures in the range of 1800 F. or above in the presence of oxidizing atmospheres.
  • Such components generally manufactured from temperature resistant iron, nickel or cobalt base alloys known as superalloys, are expected to operate without significant loss in cross-section for a minimum of 150 hours. Such a performance cannot be obtained unless these superalloys are shielded from oxidation and erosion by protective coatings or surface treatments.
  • Coatings or protective surfaces employed must, of course, protect the base metal. However, they must not weaken nor contribute any deleterious effect to it. In applications relating to flight, design requirements of components place severe restrictions on weight. Consequently, strict limitation is placed on coating thickness.
  • Another object is to provide for a superalloy surface an improved treatment method which can be applied to superalloy articles having small passages or openings such that 3,415,672 Patented Dec. 10, 1968 the openings are not clogged in processing and that the treatment method functions within the openings and passages as well as on the other surfaces of the article.
  • Still another object is to provide an article having an improved surface, resistant to oxidation conditions at temperatures of about 1800 F. and above with little, if any, addition of weight.
  • FIG. 1 is a photomicrographic view including a surface treated according to this invention taken prior to oxidation testing;
  • FIG. 2 is a photomicrographic view including the surface of FIG. 1 taken after oxidation testing.
  • FIG. 3 is a photomicrographic view of untreated base metal after oxidation testing.
  • the present invention provides a method for treating a metallic article surface based on a metal from the group iron, nickel and cobalt substantially to reproduce the original dimensions and surface finish while providing an oxidation protective surface.
  • the method includes the step of codepositing titanium and aluminum onto the article surface in a nonox-idizing atmosphere from a vapor state of a binary titanium-aluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum, with the balance titanium, in the presence of a halide salt activator selected from the group NaF, KF and NH Cl.
  • the present invention comprises, in a method for treating a metallic article surface based on the metal of the group iron, nickel and cobalt, the step of co-depositing titanium and aluminum onto the article surface in a non-oxidizing atmosphere and at a temperature of about 1750-215 0 F. from a vapor state of a powdered binary titanium-aluminum alloy consisting essentially of about 30-35 weight percent aluminum with the balance titanium in the presence of a halide salt activator from the group NaF, KF and NH Cl.
  • gaseous metal halide generated from the alloys of the specific compositions As the energy of formation of any metal halide differs from that of the other, and titanium and aluminum solutions are not ideal, the compositions of the mixture of halide gases produced from interaction of halogens with such alloys will not be proportional with that of the solid mixture. Any estimate of the ultimate coating composition will be uncertain from this effect alone. But gas composition is not the only factor which will have a large effect on the nature and composition of any coating. Among these are the kinetics of pyrolysis of each of the gaseous species, the free energy of interaction of deposited metal with the substrate and the diffusion characteristics of each deposited metal when in the presence of the other.
  • the method of the present invention including the use of a binary alloy consisting of greater than 15 and less than 50 weight percent aluminum, with the balance titanium, in the presence of a halide salt selected from NaF, KF and NH Cl when heated together Within the range of 1750-2150 F. in a non-oxidizing atmosphere, results in an easily control-led oxidation resistant coating particularly for that group of alloys known as the superalloys.
  • a halide salt selected from NaF, KF and NH Cl
  • halogen salts as NaCl, KCl, the iodides and the bromides have been tested and, though closely related to the halides used in this invention, they do not function adequately as activators in the practice of the method of the present invention.
  • the method of the present invention involves the codeposition of aluminum and titanium from a binary Ti-Al alloy first converted to its vapor state prior to deposition and through the use of a halide salt activator selected from NH Cl, NaF and its closely related compound KF. It has been found that this type of co-deposition can best be accomplished with the binary alloy in powdered form and in the Well known process involving fluidized beds or the pack cementation type process. Of these two, the pack process is the most economically conducted and was generally used in the study of the present invention.
  • EXAMPLE 1 Specimens of a nickel base superalloy having a nominal composition, by weight, of 0.15-0.20% C, 8ll% Cr, 4.5-5.0% Ti, 6% Al, 1317% Co, 24% Mo, balance Ni, were in the form of cast flat specimens and of test bars, the latter being the conventional 0.252 cylindrical type with threaded shanks for tensile testing. A binary 35 weight percent aluminum, 65 weight percent titanium alloy was cast and reduced in a crusher until particles of size 100+200 were obtained. A powdered pack mixture was made with the following ingredients in percent by weight:
  • the alumina mesh size was 150+200.
  • the pack composition was mixed thoroughly for several hours in a blender prior to introduction of the mixture into a retort in which the specimens were placed. Prior to placement of the specimens in the retort, they were vapor blasted, washed with water and rinsed with acetone. After placing the specimens in the retort With the pack composition, the retort was sealed, evacuated and back filled with argon. The retort was placed in a furnace in which the internal temperature of the retort was allowed to reach 1975 F. where it was maintained for 1 hour. The retort was then cooled rapidly to about 1400" F. in about 10 minutes then the retort was opened and the specimens were removed. The surface of the specimens were uniformly treated with a thickness change of no more than 0.0005" per side.
  • the high degree of control of treated surface thickness is achieved by the present invention through the co-deposition from a vapor state of a titanium-aluminum binary alloy containing aluminum in excess of 15% and less than 50% by weight with the balance titanium; conducted in a non-oxidizing atmosphere.
  • the following Table I compares treated surface conditions with the binary alloy used in the co-deposition onto a nickel base superalloy having a nominal composition, by weight, of 19% Cr, 11% Co, 10% Mo, 3% Ti, 1.5% A1, 3% Fe with the balance nickel sometimes referred to as Ren 41 nickel base alloy.
  • the binary alloys of Table I were used in the pack process described in Example 1 above at a temperature of about 1975 F. for about 1 hour in an argon atmosphere.
  • alloys A, B and E of Table I resulted in unsatisfactory surface conditions because of poor reproducibility or very slow deposition (alloys A and B) or because of a wide variation in thickness, too thick a coating and excess aluminum in the coating (alloy E).
  • alloys C and D within the preferred range of about 30-35 weight percent aluminum, with the balance titanium resulted in a uniform, easily controlled surface treatment with no more than about 0.001" total change in thickness.
  • alloys C and D had the ability, in the method of the present invention, to penetrate and coat narrow internal passages and openings in articles.
  • Example 2 The procedure of Example 1 was repeated with variations in the composition of the binary alloy added to the pack. The results with regard to weight change and thickness change are shown in Table II.
  • the binary alloy form of 35 weight percent aluminum-65 weight percent titanium showed a very uniform rate of deposition and a change nominal composition, by weight, of 19% Cr, 19% Co, 4%
  • Example 1 before placement in the pack. Measurement of Subsequent specimens prepared with holes of 5, and thickness and weight of specimens were made before and mils in diameter from the same material were processed after treatment in order that the weight gain of diffused as in Example 1. Not only was the exterior of the specimaterial could be determined. The specimens were treated mens coated uniformly but also the interior walls of the as in Example 2, using an aluminum oxide barrier bepassages were coated uniformly without clogging the 10 tween the specimens and the pack mixture. holes.
  • EXAMPLE 2 TABLE III Specimens in the shape of an airfoil to simulate a vane [Weight gain l fl portion of a blading member, such as an axial flow com- Activators pressor blade, were made from 0.060" sheets of the above 15 Alloy N301 ME NH 01 described Ren 41 nickel base superalloy. The specimens 4 were vapor blasted with 400 mesh alumina and rinsed 35A1-65Ti 3-1 g-g with acetone.
  • the binary Ti35% Al alloy powder of 1 Example 1 was used in the powdered pack mixture which [15 6 had the following ingredients in percent by weight: 63A 37m g g2 60% alumina 011 ii 913 38% binary Ti-Al alloy 2% anhydrous NaF actlvator
  • Table III shows that for NaF, the amount Prior to placing the specimens in the retort with the of coating deposited increases with aluminum content of powdered pack mixture as in Example 1, an aluminum the titanium-aluminum alloy but not proportionally.
  • the data is scattered indicating either the formation surface in order to prohibit adherence of the pack mixture of the metal chloride gas or that the decomposition energy to a surface of this type of an alloy.
  • the A1 0 barrier or of the chloride may be the limiting factor.
  • the blanket was applied by dipping the specimens in a slurry NH Cl data indicates the critical factor is the rate of having the following composition: formation of the metal halide.
  • the six combinations of metal alloys and activators were exposed to a cyclic oxidation test for 150 hours at 2;: g; g g ifl gg i gi oxide 1800 F. in a flame tunnel with a one minute cooling and g heating cycle between 1800 F. and 1000 F. every thirty After dlpping 1n the slurry the specimens were placed minutes.
  • Table IV compares the oxidation in an oven and baked for 2 hours at 270 F. 5 resistance of the six combinations after such tests.
  • the retort was coatings of uniformity, excellent oxidation resistance and placed in a furnace at 2150 F. under a retort pressure of good surface treatment thickness. However, it is to be 5-10 p.s.i. of argon.
  • the furnace temperature was adnoted that NaCl when used as an activator does not result justed to maintain the temperature inside the retort at in a satisfactory coating of adequate oxidation resistance. 1950 F. where it was held for 3 hours.
  • the retort Coatings from the 63 Al-37 Ti binary alloy were was cooled to 1400 F. in about 10 minutes after which coarse, irregular and exhibited excessive diffusion charthe specimens were removed from the retort.
  • Binary composition rr p g to TiAl and TiAla, TABLE V.-CYCLIC OXIDATION RESISTANCE or 35A165T1 representing two eutectic alloys of titanium and aluminum WITH aF ACTIVATOR were selected and prepared by first reducing to chips and Oy to 00 then ball milling to approximately 100 mesh for incorporation into the powdered pack mixture of Example 1.
  • Specimen Wt. Gain 'i iic i i iiiiiifiliiii These two binary alloy compositions in percent by weight Number (mg/emf) Eff Egg (mu/Side) are as follows: 35 Al-65 Ti and 63 Al37 Ti.
  • FIG. 1 shows the condition of the treated specimen of Example 2 before the above described cyclic oxidation treatment.
  • FIG. 2 shows the excellent condition of that same specimen after 100 hours cyclic oxidation testing and
  • FIG. 3 shows the oxidation intergranular attack and alloy depleted condition of the surface of an untreated specimen after 100 hours of the same oxidation testing.
  • Example 2 59.8% alumina 40% 35 Al-65 Ti binary alloy 0.2% NH Cl The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1950 F. for 3 hours. Upon removal and subsequent testing, the cobalt base alloy specimens were found to have the same surface uniformity and oxidation resistance as was indicated in the examples above.
  • EXAMPLE 5 Specimens A2" in diameter and 1" long made from an iron base alloy having a nominal composition, by weight, of 0.8% C, 4.1 Cr, 1.1% V, 4.25% Mo with the balance Fe were prepared as in Example 1 and placed in a retort with a powdered pack mixture of the following ingredients in percent by weight:
  • Example 2 58% alumina 40% 35 Al-65 Ti binary alloys 2% NaF The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1750 F. for /2 hour. Upon removal and subsequent testing, the iron base alloy specimen was found to have an excellent surface treatment an-d to have the same thickness and surface uniformity as was indicated in the examples above.
  • the mesh size of the powders used either in the pack or in the alumina barrier dip coat is not critical, the mesh size being varied from about +60 to about 200 without any noticeable difference in effect.
  • the inert barrier for example of alumina, was found to be useful during processing to control the rate of diffusion and thus to control coating thickness.
  • a shield or shim conforming to the shape of an article or various other means can be used for the same purpose.
  • This barrier was found to be particularly useful in connection with certain nickel base alloys, for example, that of the type shown in Example 2, when used with NaF activator to inhibit any adherence of the pack material to the surface of the article.
  • Such a barrier coating was found generally not to be necessary with the use of NH CI activator.
  • the present invention is significantly useful in the protection of articles made from alloys based on iron, nickel or cobalt. However, it can also be very useful in the protection of articles made from materials based on other elements, for example, the refractory metals Cr, Mo, Cb, etc. This can be accomplished by first providing a surface of iron, nickel or cobalt, or its alloys on the article and then co-depositing from a vapor state onto the surface of an alloy of Ti and Al as described above.
  • EXAMPLE 6 A specimen in the shape of a turbine blade made from a chromium base alloy having a nominal composition, by weight, of 7.5% W, 0.2% Ti, 0.8% Zr, 0.1% C, 0.3% Y with the balance Cr was cleaned by first ultrasonic cleaning and then electropolishing in NaOH followed by a dip in a solution of HCl. The specimen was given a nickel strike in a Woods solution and then electroplated with nickel in a sulfamate bath at about 0.8 amp/in. for about 1.5 hours at a temperature of F. After plating, the specimen was placed in the powdered pack mixture described in Example 2 and placed in a retort.
  • Example 2 The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1750 F. for 1 hour. Upon removal, the specimen was found to have an excellent surface treatment and to have the same surface uniformity, lack of substantial change in thickness and excellent oxidation resistance as was indicated in the examples above.
  • a method of treating a metallic article surface of a material based on a metal selected from a group consisting of iron, nickel and cobalt the step of co-depositing titanium and aluminum onto the article surface in a nonoxidizing atmosphere and at a temperature of about 17502150 F. from a vapor state of a binary titaniumaluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum, with the balance titanium, in the presence of a halide salt activator selected from the group consisting of NaF, KF and NH Cl.
  • a method for treating a metallic article surface of a material based on a metal selected from the group consisting of iron, nickel and cobalt comprising the steps of:
  • alumina 50-60% alumina; 1 (b) 38-40% of a powdered binary titaniumaluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum with the balance titanium; and (c) 02-10% of a halide salt activator selected from the group consisting of NaF, KF and NH Cl; heating the article and powder mixture at a temperature of about 1750-2150 F. in an inert atmosphere for about 1-4 hours to vaporize at least a part of the binary alloy; and then cooling the article prior to removal from the inert atmosphere.
  • a halide salt activator selected from the group consisting of NaF, KF and NH Cl
  • the binary titanium alloy in the powder mixture consists essentially of, by weight, 3035% aluminum, with the balance titanium; the halide salt activator is NH CI; and the temperature is about 1750-1975 F.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Chemically Coating (AREA)
  • Powder Metallurgy (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)

Description

63 LEVINSTEIN ETAL 3,415,672 Dec 10 METHOD OF c -D loslTINfi TITANIUM AND ALUMINUM 0N SURFACES OF NICKEL, IRON AND COBALT Filed Nov. 12, 1964 SPECIMEN AS Taefigg SURFACE DIFFUSED ZONE UNAFFECTED BASE METAL 11- TREATED- DIFFUSED '15 z TREATED SPECIMEN AFTER I800 F CYCLIC OXIDATION Ii-A1 TREATED- DIFFUSED SURACE DIFFUSED ZONE SECON DA RY DIFFUSION ZONE UNAFFECTED BASE METAL I q 3 UNTREATED SPECIMEN AFTER I800 F CYCLIC OXIDATION OXIDATION INT ERGRANULAR ATTACK BASE METAL INVENTORJ- M0555 A (EV/#5727 BY J49 M 6 5/7/58 United States Patent 3 415,672 METHOD OF CO-DElOSITING TITANIUM AND ALUMINUM ON SURFACES OF NICKEL, IRON AND COBALT Moses A. Levinstein and John W. Grenier, Cincinnati,
Ohio, assignors to General Electric Company, a corporation of New York Filed Nov. 12, 1964, Ser. No. 410,645 9 Claims. (Cl. 117-71) ABSTRACT OF THE DISCLOSURE The method for treating a metallic surface of a material based on iron, nickel or cobalt involves co-depositing Ti and Al in a non-oxidizing atmosphere onto such surface from a binary Ti-Al alloy in the vapor state through such a halide salt activator as NaF, KF and NH Cl.
This invention relates to the treatment of metallic surfaces, and more particularly, to the treatment with a binary Ti-Al alloy of metallic surfaces based on alloys of iron, nickel and cobalt.
Components of modern power producing apparatus, for example turbine components of jet engines, are exposed to temperatures in the range of 1800 F. or above in the presence of oxidizing atmospheres. Such components, generally manufactured from temperature resistant iron, nickel or cobalt base alloys known as superalloys, are expected to operate without significant loss in cross-section for a minimum of 150 hours. Such a performance cannot be obtained unless these superalloys are shielded from oxidation and erosion by protective coatings or surface treatments.
Coatings or protective surfaces employed must, of course, protect the base metal. However, they must not weaken nor contribute any deleterious effect to it. In applications relating to flight, design requirements of components place severe restrictions on weight. Consequently, strict limitation is placed on coating thickness.
A wide variety of coatings of the type which add to the dimensions and weight of an article have been reported. For example, many varieties applied by electrodeposition, molten baths, flame spraying, cladding and similar procedures, singly or in various combinations are well known. While some coatings of these types can withstand the desired operating conditions, they nevertheless change the finished dimensions and add to the weight of the article. In addition, known coatings and surface treatments are difficult or impossible to apply in small passages within articles. Furthermore, the edge thickening effects and the clogging of narrow openings or passages have been troublesome with known coatings. For example, the use of molten bath type processes results in excessive surface build-up and blockage of narrow passages. Cladding is difficult, costly and cannot be used to cover narrow passages. Electrodeposition cannot plate in narrow passages and electroless deposition has thermal limitations. Relatively poor control over some pack cementat-ion type processes results in undesirable coating properties and characteristics.
Therefore, it is a principal object of the present invention to provide for a superalloy surface an improved treatment method which substantially reproduces the original dimension and surface finish prior to treatment yet which provides protection for article surfaces based on iron, cobalt or nickel base alloys in the temperature range of 1800 F. and above for a minimum of 150 hours in air.
Another object is to provide for a superalloy surface an improved treatment method which can be applied to superalloy articles having small passages or openings such that 3,415,672 Patented Dec. 10, 1968 the openings are not clogged in processing and that the treatment method functions within the openings and passages as well as on the other surfaces of the article.
Still another object is to provide an article having an improved surface, resistant to oxidation conditions at temperatures of about 1800 F. and above with little, if any, addition of weight.
These and other objects and advantages will be more clearly understood from the following detailed description, examples and drawing which are meant to be exemplary of rather than any limitation on the scope of the present invention.
In the drawing:
FIG. 1 is a photomicrographic view including a surface treated according to this invention taken prior to oxidation testing;
FIG. 2 is a photomicrographic view including the surface of FIG. 1 taken after oxidation testing; and
FIG. 3 is a photomicrographic view of untreated base metal after oxidation testing.
Briefly, in its broader aspects the present invention provides a method for treating a metallic article surface based on a metal from the group iron, nickel and cobalt substantially to reproduce the original dimensions and surface finish while providing an oxidation protective surface. The method includes the step of codepositing titanium and aluminum onto the article surface in a nonox-idizing atmosphere from a vapor state of a binary titanium-aluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum, with the balance titanium, in the presence of a halide salt activator selected from the group NaF, KF and NH Cl.
In its preferred form, the present invention comprises, in a method for treating a metallic article surface based on the metal of the group iron, nickel and cobalt, the step of co-depositing titanium and aluminum onto the article surface in a non-oxidizing atmosphere and at a temperature of about 1750-215 0 F. from a vapor state of a powdered binary titanium-aluminum alloy consisting essentially of about 30-35 weight percent aluminum with the balance titanium in the presence of a halide salt activator from the group NaF, KF and NH Cl.
The application of the combination of titanium and aluminum as a surface treatment or coating has been previously reported. For example, there are known molten bath applications and pack treatments, the latter with the titanium in the form of ferro-titanium or nickel titanium alloys including aluminum as well. However, the presence in the treated surface of a material such as iron, nickel, manganese, silicon and the like prohibits close control of treatment of the surface or coating. It has been found that the use of a binary Ti-Al alloy within a specified composition range and a particular group of halide salts affords unexpected accuracy in treatment control while affording improved oxidation resistance. Therefore the present invention specifically avoids the inclusion of elements other than aluminum and titanium in the vaporized alloy in order to accurately control the extent of surface treatment.
From this unexpected finding, it would appear as if a coating of any desired composition could be produced by a pack-cementation process. It is believed, with regard to the present invention, that the two elements of the coating, titanium and aluminum when placed in a pack with a suitable activator at high temperatures will react with the activator to form the metal halides. The halide gases, in turn, are believed to decompose and deposit a metal or alloy on the surface to be treated. The temperature at which the method of the present invention is conducted, is between 1750 F. and the temperature above which the base metal is undesirably affected. Generally and practically, this range is about 1750-2150 F. Penetration of 3 the base metal by the deposited metal produces a surface through which the deposited metal has diffused.
It would seem, superfically, that this process could be generally predicted from knowledge of the characteristics of halide salts and their reactions with metals, as well as the diffusion rates of metals and alloys one into the other. However, this is not so for there are a number of significant deviations which can be expected to prohibit prediction of the present invention. Assuming ideal thermodynamic behavior throughout, it might appear capable of hypothesis that the composition of the composite will be controlled by the composition of the gaseous halide mixture. This mixture is determined by the concentration of each coating constituent in the pack. On closer examination, deviation from ideality can be expected to be considerable.
With regard to the gaseous metal halide generated from the alloys of the specific compositions, as the energy of formation of any metal halide differs from that of the other, and titanium and aluminum solutions are not ideal, the compositions of the mixture of halide gases produced from interaction of halogens with such alloys will not be proportional with that of the solid mixture. Any estimate of the ultimate coating composition will be uncertain from this effect alone. But gas composition is not the only factor which will have a large effect on the nature and composition of any coating. Among these are the kinetics of pyrolysis of each of the gaseous species, the free energy of interaction of deposited metal with the substrate and the diffusion characteristics of each deposited metal when in the presence of the other.
It has been found, however, that the method of the present invention including the use of a binary alloy consisting of greater than 15 and less than 50 weight percent aluminum, with the balance titanium, in the presence of a halide salt selected from NaF, KF and NH Cl when heated together Within the range of 1750-2150 F. in a non-oxidizing atmosphere, results in an easily control-led oxidation resistant coating particularly for that group of alloys known as the superalloys. In subsequent examples, it Will be shown that this particular selection of halogen salts can be used in the practice of the present invention. However, such halogen salts as NaCl, KCl, the iodides and the bromides have been tested and, though closely related to the halides used in this invention, they do not function adequately as activators in the practice of the method of the present invention.
The method of the present invention involves the codeposition of aluminum and titanium from a binary Ti-Al alloy first converted to its vapor state prior to deposition and through the use of a halide salt activator selected from NH Cl, NaF and its closely related compound KF. It has been found that this type of co-deposition can best be accomplished with the binary alloy in powdered form and in the Well known process involving fluidized beds or the pack cementation type process. Of these two, the pack process is the most economically conducted and was generally used in the study of the present invention.
EXAMPLE 1 Specimens of a nickel base superalloy having a nominal composition, by weight, of 0.15-0.20% C, 8ll% Cr, 4.5-5.0% Ti, 6% Al, 1317% Co, 24% Mo, balance Ni, were in the form of cast flat specimens and of test bars, the latter being the conventional 0.252 cylindrical type with threaded shanks for tensile testing. A binary 35 weight percent aluminum, 65 weight percent titanium alloy was cast and reduced in a crusher until particles of size 100+200 were obtained. A powdered pack mixture was made with the following ingredients in percent by weight:
50% alumina 40% binary Ti-Al alloy sodium fluoride activator The alumina mesh size was 150+200. The pack composition was mixed thoroughly for several hours in a blender prior to introduction of the mixture into a retort in which the specimens were placed. Prior to placement of the specimens in the retort, they were vapor blasted, washed with water and rinsed with acetone. After placing the specimens in the retort With the pack composition, the retort was sealed, evacuated and back filled with argon. The retort was placed in a furnace in which the internal temperature of the retort was allowed to reach 1975 F. where it was maintained for 1 hour. The retort was then cooled rapidly to about 1400" F. in about 10 minutes then the retort was opened and the specimens were removed. The surface of the specimens were uniformly treated with a thickness change of no more than 0.0005" per side.
The high degree of control of treated surface thickness is achieved by the present invention through the co-deposition from a vapor state of a titanium-aluminum binary alloy containing aluminum in excess of 15% and less than 50% by weight with the balance titanium; conducted in a non-oxidizing atmosphere. The following Table I compares treated surface conditions with the binary alloy used in the co-deposition onto a nickel base superalloy having a nominal composition, by weight, of 19% Cr, 11% Co, 10% Mo, 3% Ti, 1.5% A1, 3% Fe with the balance nickel sometimes referred to as Ren 41 nickel base alloy.
TABLE I.SURFAOE CONDITION COMPARISON Binary Wt. Percent Alloy Remarks 10 90 Very slow deposition. 15 Poor reproducibility. 3O 70 }Uniform coverage, good deposition rate, 38 easily controlled. 5
WiAiIe variation in thickness; too thick excess;
The binary alloys of Table I were used in the pack process described in Example 1 above at a temperature of about 1975 F. for about 1 hour in an argon atmosphere.
The use of binary alloys A, B and E of Table I resulted in unsatisfactory surface conditions because of poor reproducibility or very slow deposition (alloys A and B) or because of a wide variation in thickness, too thick a coating and excess aluminum in the coating (alloy E). On the other hand, the use of alloys C and D within the preferred range of about 30-35 weight percent aluminum, with the balance titanium resulted in a uniform, easily controlled surface treatment with no more than about 0.001" total change in thickness. Furthermore, alloys C and D had the ability, in the method of the present invention, to penetrate and coat narrow internal passages and openings in articles.
The procedure of Example 1 was repeated with variations in the composition of the binary alloy added to the pack. The results with regard to weight change and thickness change are shown in Table II.
It should be noted that the binary alloy form of 35 weight percent aluminum-65 weight percent titanium showed a very uniform rate of deposition and a change nominal composition, by weight, of 19% Cr, 19% Co, 4%
in thickness per side of less than 0.0005". This was true M0, 3.5% Ti, 2.9% A1, 0.1% C, up to 4% Fe, with the even after 4 hours of treatment. On the other hand, the balance Ni was used as specimen material in this example. 90% All% Ti alloy showed a significantly larger Cast specimen strips of approximately 0.070" x 0.375" x weight gain during processing with a significantly larger 2.0" were polished flat and were washed and dried as in and undesirable change in dimensions. Example 1 before placement in the pack. Measurement of Subsequent specimens prepared with holes of 5, and thickness and weight of specimens were made before and mils in diameter from the same material were processed after treatment in order that the weight gain of diffused as in Example 1. Not only was the exterior of the specimaterial could be determined. The specimens were treated mens coated uniformly but also the interior walls of the as in Example 2, using an aluminum oxide barrier bepassages were coated uniformly without clogging the 10 tween the specimens and the pack mixture. holes.
EXAMPLE 2 TABLE III Specimens in the shape of an airfoil to simulate a vane [Weight gain l fl portion of a blading member, such as an axial flow com- Activators pressor blade, were made from 0.060" sheets of the above 15 Alloy N301 ME NH 01 described Ren 41 nickel base superalloy. The specimens 4 were vapor blasted with 400 mesh alumina and rinsed 35A1-65Ti 3-1 g-g with acetone. The binary Ti35% Al alloy powder of 1 Example 1 was used in the powdered pack mixture which [15 6 had the following ingredients in percent by weight: 63A 37m g g2 60% alumina 011 ii 913 38% binary Ti-Al alloy 2% anhydrous NaF actlvator The above Table III shows that for NaF, the amount Prior to placing the specimens in the retort with the of coating deposited increases with aluminum content of powdered pack mixture as in Example 1, an aluminum the titanium-aluminum alloy but not proportionally. For oxide slurry blanket or barrier was applied to the specimen NaCl, the data is scattered indicating either the formation surface in order to prohibit adherence of the pack mixture of the metal chloride gas or that the decomposition energy to a surface of this type of an alloy. The A1 0 barrier or of the chloride may be the limiting factor. However, the blanket was applied by dipping the specimens in a slurry NH Cl data indicates the critical factor is the rate of having the following composition: formation of the metal halide.
The six combinations of metal alloys and activators were exposed to a cyclic oxidation test for 150 hours at 2;: g; g g ifl gg i gi oxide 1800 F. in a flame tunnel with a one minute cooling and g heating cycle between 1800 F. and 1000 F. every thirty After dlpping 1n the slurry the specimens were placed minutes. The following Table IV compares the oxidation in an oven and baked for 2 hours at 270 F. 5 resistance of the six combinations after such tests.
70 grams methylcellulose TABLE IV.THICKNESS AND OXIDATION RESISTANCE NACI NAF NH4Cl Thickness Oxidation Thickness Oxidation Thickness Oxidation gain (mils) resistance gain (mils) resistance gain (mils) resistance iitiiiitiiiiiiij 3' 3 11 33333: 13% fi fittteiii: iii ii' After this pretreatment, the specimens were placed in Tables III and 1V show that the Al-65 Ti binary the retort with the pack mixture and the retort was closed, alloy, particularly using NaF as the activator, produced evacuated and back filled with argon. The retort Was coatings of uniformity, excellent oxidation resistance and placed in a furnace at 2150 F. under a retort pressure of good surface treatment thickness. However, it is to be 5-10 p.s.i. of argon. The furnace temperature was adnoted that NaCl when used as an activator does not result justed to maintain the temperature inside the retort at in a satisfactory coating of adequate oxidation resistance. 1950 F. where it was held for 3 hours. Then the retort Coatings from the 63 Al-37 Ti binary alloy were was cooled to 1400 F. in about 10 minutes after which coarse, irregular and exhibited excessive diffusion charthe specimens were removed from the retort. Because acteristics in the oxidation tests. On the other hand, the such heating removed the methylcellulose binder and water 35 A165 Ti binary alloy showed less than 0.4 mil sec from the alumina blanket surrounding the specimens, the ondary diffusion in the oxidation tests. This is more clearly alumina was easily brushed from the surface of the shown in Table V below. The 35 Al-65 Ti binary alloy specimen. was studied further with regard to oxidation resistance EXAMPLE 3 using NaF as an activator. The results of these studies are 65 shown in the following Table V. Binary composition rr p g to TiAl and TiAla, TABLE V.-CYCLIC OXIDATION RESISTANCE or 35A165T1 representing two eutectic alloys of titanium and aluminum WITH aF ACTIVATOR were selected and prepared by first reducing to chips and Oy to 00 then ball milling to approximately 100 mesh for incorporation into the powdered pack mixture of Example 1. Specimen Wt. Gain 'i iic i i iiiiifiliii These two binary alloy compositions in percent by weight Number (mg/emf) Eff Egg (mu/Side) are as follows: 35 Al-65 Ti and 63 Al37 Ti. Each of these compositions was deposited in the presence of activators 8: 8:3 8-: NaF, NaCl and NH Cl. A nickel base alloy having a 8-1? 3 81% After successful testing in this series, the surface was in excellent condition and the base metal was well protected. The oxidation behavior of this binary alloy was particularly gratifying. Table V lists the small weight gain, small dimensional changes and very small degree of secondary diffusion. Even though the oxidation resistance tends to be enhanced by the presence of a thicker treated portion, nevertheless even at a treatment thickness of 0.8 mil more particularly shown in the Table VI below, the coating provided good protection for at least 150 hours at 1800 F. The small secondary diffusion is quite important because it shows that the presence of titanium with aluminum is sufficient to inhibit the ditfusion of aluminum. This result was not expected and could not be predicted because it was believed prior to this that the function of the titanium in a TiAl system was as a barrier to the diffusion of aluminum into the base metal. These data indicate that the mere presence of titanium in the proper proportions is enough.
Reproducibility runs were made with the cast specimens of the same length, width and thickness described above, polished flat and parallel within 0.0005". The results of this testing are shown in the following Table VI.
TABLE VI.REPRODUCIBILITY OF 35Al-65Ti WITH NaF AGTIVA'IOR Specimen Weight Gain Thickness Change (mils) Number (mg/cm!) Specimen Coating 2. 7 None 0. 8-1. 2. 3 None 0. 7-0. 8 2. 2 None 0. 8-0. 9 2. 2 None 0. 8-0. 9 2. 1 None 0. 8-1. 0 2. 0 None 0. 7 -0. 8 2. 1 None 0. 6-0. 8 2. 0 None 0. 6-0. 8
The condition of the treated specimen of Example 2 before the above described cyclic oxidation treatment is shown in the photomicrograph of FIG. 1 at a magnification of 250x. FIG. 2 shows the excellent condition of that same specimen after 100 hours cyclic oxidation testing and FIG. 3 shows the oxidation intergranular attack and alloy depleted condition of the surface of an untreated specimen after 100 hours of the same oxidation testing. These specimens were etched with 3% H 0 EXAMPLE 4 Specimen 'buttons in diameter and 0.25" thick made from a cobalt base alloy having a nominal composition, by weight, of 0.5% C, 25% Cr, 10% Ni, 8% W with the balance Co were prepared as in Example 1, and placed in a retort with a powdered pack mixture of the following ingredients in percent by weight:
59.8% alumina 40% 35 Al-65 Ti binary alloy 0.2% NH Cl The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1950 F. for 3 hours. Upon removal and subsequent testing, the cobalt base alloy specimens were found to have the same surface uniformity and oxidation resistance as was indicated in the examples above.
EXAMPLE 5 Specimens A2" in diameter and 1" long made from an iron base alloy having a nominal composition, by weight, of 0.8% C, 4.1 Cr, 1.1% V, 4.25% Mo with the balance Fe were prepared as in Example 1 and placed in a retort with a powdered pack mixture of the following ingredients in percent by weight:
58% alumina 40% 35 Al-65 Ti binary alloys 2% NaF The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1750 F. for /2 hour. Upon removal and subsequent testing, the iron base alloy specimen was found to have an excellent surface treatment an-d to have the same thickness and surface uniformity as was indicated in the examples above.
During evaluation of the method of the present invention, it was found that the mesh size of the powders used either in the pack or in the alumina barrier dip coat is not critical, the mesh size being varied from about +60 to about 200 without any noticeable difference in effect. The inert barrier, for example of alumina, was found to be useful during processing to control the rate of diffusion and thus to control coating thickness. A shield or shim conforming to the shape of an article or various other means can be used for the same purpose. This barrier was found to be particularly useful in connection with certain nickel base alloys, for example, that of the type shown in Example 2, when used with NaF activator to inhibit any adherence of the pack material to the surface of the article. Such a barrier coating was found generally not to be necessary with the use of NH CI activator.
The present invention is significantly useful in the protection of articles made from alloys based on iron, nickel or cobalt. However, it can also be very useful in the protection of articles made from materials based on other elements, for example, the refractory metals Cr, Mo, Cb, etc. This can be accomplished by first providing a surface of iron, nickel or cobalt, or its alloys on the article and then co-depositing from a vapor state onto the surface of an alloy of Ti and Al as described above.
EXAMPLE 6 A specimen in the shape of a turbine blade made from a chromium base alloy having a nominal composition, by weight, of 7.5% W, 0.2% Ti, 0.8% Zr, 0.1% C, 0.3% Y with the balance Cr was cleaned by first ultrasonic cleaning and then electropolishing in NaOH followed by a dip in a solution of HCl. The specimen was given a nickel strike in a Woods solution and then electroplated with nickel in a sulfamate bath at about 0.8 amp/in. for about 1.5 hours at a temperature of F. After plating, the specimen was placed in the powdered pack mixture described in Example 2 and placed in a retort. The same procedure was followed as in Example 1 except that the temperature within the retort was maintained at 1750 F. for 1 hour. Upon removal, the specimen was found to have an excellent surface treatment and to have the same surface uniformity, lack of substantial change in thickness and excellent oxidation resistance as was indicated in the examples above.
Although the present invention has been described in connection with specific examples and embodiments, it will be understood by those skilled in the arts of metallurgy and surface treatment the various modifications and variations of which the present invention is capable.
What is claimed is:
1. In a method of treating a metallic article surface of a material based on a metal selected from a group consisting of iron, nickel and cobalt, the step of co-depositing titanium and aluminum onto the article surface in a nonoxidizing atmosphere and at a temperature of about 17502150 F. from a vapor state of a binary titaniumaluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum, with the balance titanium, in the presence of a halide salt activator selected from the group consisting of NaF, KF and NH Cl.
2. The method of claim 1 in which the binary titaniumaluminum alloy is powdered and consists essentially of, by weight, about 30-35% aluminum, with the balance titanium.
3. The method of claim 2 in which the temperature is about 1750-1975 F. and the halide salt activator is NaF.
4. The method of claim 2 in which the temperature is about 1750-1975" F. and the halide salt activator is NH Cl.
5. A method for treating a metallic article surface of a material based on a metal selected from the group consisting of iron, nickel and cobalt, comprising the steps of:
cleaning the surface;
immersing the article in a powder mixture consisting of, by weight,
(a) 50-60% alumina; 1 (b) 38-40% of a powdered binary titaniumaluminum alloy consisting essentially of, by weight, more than 15% and less than 50% aluminum with the balance titanium; and (c) 02-10% of a halide salt activator selected from the group consisting of NaF, KF and NH Cl; heating the article and powder mixture at a temperature of about 1750-2150 F. in an inert atmosphere for about 1-4 hours to vaporize at least a part of the binary alloy; and then cooling the article prior to removal from the inert atmosphere.
6. The method of claim 5 in which an inert barrier material is located between the article surface and the powdered mixture and the temperature is from about 1750-1975 F.
7. The method of claim 5 in which the binary titanium alloy in the powder mixture consists essentially of, by weight, 3035% aluminum, with the balance titanium; the halide salt activator is NH CI; and the temperature is about 1750-1975 F.
8. The method of claim 6 in which the binary titaniumaluminum alloy in the powder mixture is 30-35% aluminum, with the balance titanium; and the halide salt activator is NaF.
9. The method of claim 5 in which the metallic article surface material is first deposited on an article prior to immersing the article in the powder mixture.
References Cited UNITED STATES PATENTS RALPH S. KENDALL, Primary Examiner.
I. R. BATTEN, JR., Assistant Examiner.
US. Cl. X.R.
US410645A 1964-11-12 1964-11-12 Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt Expired - Lifetime US3415672A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US410645A US3415672A (en) 1964-11-12 1964-11-12 Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt
GB42583/65A GB1100176A (en) 1964-11-12 1965-10-07 Diffusion coating of metals
BE672291D BE672291A (en) 1964-11-12 1965-11-12
DE19651521269 DE1521269C3 (en) 1964-11-12 1965-11-12 Process for the formation of protective layers on metal objects based on iron, nickel or cobalt

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US410645A US3415672A (en) 1964-11-12 1964-11-12 Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt

Publications (1)

Publication Number Publication Date
US3415672A true US3415672A (en) 1968-12-10

Family

ID=23625618

Family Applications (1)

Application Number Title Priority Date Filing Date
US410645A Expired - Lifetime US3415672A (en) 1964-11-12 1964-11-12 Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt

Country Status (3)

Country Link
US (1) US3415672A (en)
BE (1) BE672291A (en)
GB (1) GB1100176A (en)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3617360A (en) * 1968-11-29 1971-11-02 Gen Electric High temperature metallic diffusion coating and method
US3718962A (en) * 1970-09-28 1973-03-06 Gen Electric High temperature metallic diffusion coating
US3753668A (en) * 1970-04-16 1973-08-21 Api Corp Diffusion coated metallic substrate
US3881882A (en) * 1973-04-19 1975-05-06 Inland Steel Co Aluminum coated steel
US4377607A (en) * 1978-11-21 1983-03-22 Fuji Photo Film Company, Ltd. Process for producing vacuum deposition films
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
EP0222241A1 (en) * 1985-10-31 1987-05-20 Air Products And Chemicals, Inc. Deposition of titanium aluminides
US4800132A (en) * 1986-10-22 1989-01-24 Macdermid, Incorporated Mechanical plating with oxidation-prone metals
US4978588A (en) * 1987-09-18 1990-12-18 Nkk Corporation Plated steel sheet for a can
US5334263A (en) * 1991-12-05 1994-08-02 General Electric Company Substrate stabilization of diffusion aluminide coated nickel-based superalloys
US5512382A (en) * 1995-05-08 1996-04-30 Alliedsignal Inc. Porous thermal barrier coating
US5562998A (en) * 1994-11-18 1996-10-08 Alliedsignal Inc. Durable thermal barrier coating
US6103386A (en) * 1994-11-18 2000-08-15 Allied Signal Inc Thermal barrier coating with alumina bond inhibitor
US6146696A (en) * 1999-05-26 2000-11-14 General Electric Company Process for simultaneously aluminizing nickel-base and cobalt-base superalloys
US6224963B1 (en) 1997-05-14 2001-05-01 Alliedsignal Inc. Laser segmented thick thermal barrier coatings for turbine shrouds
US6482537B1 (en) 2000-03-24 2002-11-19 Honeywell International, Inc. Lower conductivity barrier coating
US20040043143A1 (en) * 2002-08-30 2004-03-04 Rochester Thomas H. Mechanical deposition process
WO2005035819A1 (en) * 2003-10-11 2005-04-21 Mtu Aero Engines Gmbh Method for local alitising, siliconising and chroming of metal components
US6884461B2 (en) 2002-12-20 2005-04-26 General Electric Company Turbine nozzle with heat rejection coats
US6884515B2 (en) 2002-12-20 2005-04-26 General Electric Company Afterburner seals with heat rejection coats
US6884460B2 (en) 2002-12-20 2005-04-26 General Electric Company Combustion liner with heat rejection coats
US20060210800A1 (en) * 2005-03-21 2006-09-21 Irene Spitsberg Environmental barrier layer for silcon-containing substrate and process for preparing same
US20060211241A1 (en) * 2005-03-21 2006-09-21 Christine Govern Protective layer for barrier coating for silicon-containing substrate and process for preparing same
US20060280954A1 (en) * 2005-06-13 2006-12-14 Irene Spitsberg Corrosion resistant sealant for outer EBL of silicon-containing substrate and processes for preparing same
US20060280952A1 (en) * 2005-06-13 2006-12-14 Hazel Brian T Bond coat for corrosion resistant EBC for silicon-containing substrate and processes for preparing same
US20060280953A1 (en) * 2005-06-13 2006-12-14 Hazel Brian T Bond coat for silicon-containing substrate for EBC and processes for preparing same
US20060280955A1 (en) * 2005-06-13 2006-12-14 Irene Spitsberg Corrosion resistant sealant for EBC of silicon-containing substrate and processes for preparing same
EP1939318A2 (en) 2006-12-27 2008-07-02 General Electric Company Carburization process for stabilizing nickel-based superalloys
US20090214888A1 (en) * 2003-08-18 2009-08-27 Upchurch Charles J Method and apparatus for producing alloyed iron article
US20100221574A1 (en) * 2009-02-27 2010-09-02 Rochester Thomas H Zinc alloy mechanically deposited coatings and methods of making the same
US11970953B2 (en) * 2019-08-23 2024-04-30 Rtx Corporation Slurry based diffusion coatings for blade under platform of internally-cooled components and process therefor

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1902503A (en) * 1930-05-29 1933-03-21 Gen Electric Process for coating metals
US2874070A (en) * 1951-05-16 1959-02-17 Onera (Off Nat Aerospatiale) Method for the formation of diffusion superficial alloys, in particular chromium alloys
US2887420A (en) * 1956-04-06 1959-05-19 Bristol Aero Engines Ltd Surface treatments for articles made from heat resisting alloys
US3061463A (en) * 1959-03-26 1962-10-30 Chromalloy Corp Metallic diffusion
US3061462A (en) * 1959-03-26 1962-10-30 Chromalloy Corp Metallic diffusion processes
US3079276A (en) * 1960-10-14 1963-02-26 Union Carbide Corp Vapor diffusion coating process
US3096160A (en) * 1961-06-19 1963-07-02 Union Carbide Corp Vapor diffusion coating process
US3096205A (en) * 1960-05-16 1963-07-02 Chromalloy Corp Diffusion coating of metals
US3102044A (en) * 1960-09-12 1963-08-27 United Aircraft Corp Applying protective coating from powdered material utilizing high temperature and low pressure
US3219474A (en) * 1962-05-11 1965-11-23 Priceman Seymour Protective coatings for columbium and its alloys
US3262764A (en) * 1963-08-19 1966-07-26 United Aircraft Corp Coatings for columbium base alloys
US3263325A (en) * 1963-05-07 1966-08-02 Du Pont Method of coating and bonding refractory-base-metal articles

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1902503A (en) * 1930-05-29 1933-03-21 Gen Electric Process for coating metals
US2874070A (en) * 1951-05-16 1959-02-17 Onera (Off Nat Aerospatiale) Method for the formation of diffusion superficial alloys, in particular chromium alloys
US2887420A (en) * 1956-04-06 1959-05-19 Bristol Aero Engines Ltd Surface treatments for articles made from heat resisting alloys
US3061463A (en) * 1959-03-26 1962-10-30 Chromalloy Corp Metallic diffusion
US3061462A (en) * 1959-03-26 1962-10-30 Chromalloy Corp Metallic diffusion processes
US3096205A (en) * 1960-05-16 1963-07-02 Chromalloy Corp Diffusion coating of metals
US3102044A (en) * 1960-09-12 1963-08-27 United Aircraft Corp Applying protective coating from powdered material utilizing high temperature and low pressure
US3079276A (en) * 1960-10-14 1963-02-26 Union Carbide Corp Vapor diffusion coating process
US3096160A (en) * 1961-06-19 1963-07-02 Union Carbide Corp Vapor diffusion coating process
US3219474A (en) * 1962-05-11 1965-11-23 Priceman Seymour Protective coatings for columbium and its alloys
US3263325A (en) * 1963-05-07 1966-08-02 Du Pont Method of coating and bonding refractory-base-metal articles
US3262764A (en) * 1963-08-19 1966-07-26 United Aircraft Corp Coatings for columbium base alloys

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3617360A (en) * 1968-11-29 1971-11-02 Gen Electric High temperature metallic diffusion coating and method
US3753668A (en) * 1970-04-16 1973-08-21 Api Corp Diffusion coated metallic substrate
US3718962A (en) * 1970-09-28 1973-03-06 Gen Electric High temperature metallic diffusion coating
US3881882A (en) * 1973-04-19 1975-05-06 Inland Steel Co Aluminum coated steel
US4377607A (en) * 1978-11-21 1983-03-22 Fuji Photo Film Company, Ltd. Process for producing vacuum deposition films
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
EP0222241A1 (en) * 1985-10-31 1987-05-20 Air Products And Chemicals, Inc. Deposition of titanium aluminides
US4698244A (en) * 1985-10-31 1987-10-06 Air Products And Chemicals, Inc. Deposition of titanium aluminides
US4800132A (en) * 1986-10-22 1989-01-24 Macdermid, Incorporated Mechanical plating with oxidation-prone metals
US4978588A (en) * 1987-09-18 1990-12-18 Nkk Corporation Plated steel sheet for a can
US5334263A (en) * 1991-12-05 1994-08-02 General Electric Company Substrate stabilization of diffusion aluminide coated nickel-based superalloys
US5562998A (en) * 1994-11-18 1996-10-08 Alliedsignal Inc. Durable thermal barrier coating
US6103386A (en) * 1994-11-18 2000-08-15 Allied Signal Inc Thermal barrier coating with alumina bond inhibitor
US6395343B1 (en) 1994-11-18 2002-05-28 Alliedsignal Durable thermal barrier coating
US5512382A (en) * 1995-05-08 1996-04-30 Alliedsignal Inc. Porous thermal barrier coating
US5624721A (en) * 1995-05-08 1997-04-29 Alliedsignal Inc. Method of producing a superalloy article
US6224963B1 (en) 1997-05-14 2001-05-01 Alliedsignal Inc. Laser segmented thick thermal barrier coatings for turbine shrouds
US6146696A (en) * 1999-05-26 2000-11-14 General Electric Company Process for simultaneously aluminizing nickel-base and cobalt-base superalloys
SG84598A1 (en) * 1999-05-26 2001-11-20 Gen Electric Process for simultaneously aluminizing nickel-base and cobalt-base superalloys
US6482537B1 (en) 2000-03-24 2002-11-19 Honeywell International, Inc. Lower conductivity barrier coating
US20040043143A1 (en) * 2002-08-30 2004-03-04 Rochester Thomas H. Mechanical deposition process
US6884461B2 (en) 2002-12-20 2005-04-26 General Electric Company Turbine nozzle with heat rejection coats
US6884515B2 (en) 2002-12-20 2005-04-26 General Electric Company Afterburner seals with heat rejection coats
US6884460B2 (en) 2002-12-20 2005-04-26 General Electric Company Combustion liner with heat rejection coats
US8137765B2 (en) 2003-08-18 2012-03-20 Upchurch Charles J Method of producing alloyed iron article
US20090214888A1 (en) * 2003-08-18 2009-08-27 Upchurch Charles J Method and apparatus for producing alloyed iron article
US20070272331A1 (en) * 2003-10-11 2007-11-29 Mtu Aero Engines Gmbh Method for Local Alitation, Siliconization or Chromation of Metal Components
WO2005035819A1 (en) * 2003-10-11 2005-04-21 Mtu Aero Engines Gmbh Method for local alitising, siliconising and chroming of metal components
US20060210800A1 (en) * 2005-03-21 2006-09-21 Irene Spitsberg Environmental barrier layer for silcon-containing substrate and process for preparing same
US20060211241A1 (en) * 2005-03-21 2006-09-21 Christine Govern Protective layer for barrier coating for silicon-containing substrate and process for preparing same
US20060280953A1 (en) * 2005-06-13 2006-12-14 Hazel Brian T Bond coat for silicon-containing substrate for EBC and processes for preparing same
US20060280955A1 (en) * 2005-06-13 2006-12-14 Irene Spitsberg Corrosion resistant sealant for EBC of silicon-containing substrate and processes for preparing same
US20060280952A1 (en) * 2005-06-13 2006-12-14 Hazel Brian T Bond coat for corrosion resistant EBC for silicon-containing substrate and processes for preparing same
US7354651B2 (en) 2005-06-13 2008-04-08 General Electric Company Bond coat for corrosion resistant EBC for silicon-containing substrate and processes for preparing same
US7442444B2 (en) 2005-06-13 2008-10-28 General Electric Company Bond coat for silicon-containing substrate for EBC and processes for preparing same
US20060280954A1 (en) * 2005-06-13 2006-12-14 Irene Spitsberg Corrosion resistant sealant for outer EBL of silicon-containing substrate and processes for preparing same
EP1939318A2 (en) 2006-12-27 2008-07-02 General Electric Company Carburization process for stabilizing nickel-based superalloys
US20100221574A1 (en) * 2009-02-27 2010-09-02 Rochester Thomas H Zinc alloy mechanically deposited coatings and methods of making the same
US11970953B2 (en) * 2019-08-23 2024-04-30 Rtx Corporation Slurry based diffusion coatings for blade under platform of internally-cooled components and process therefor
US12320271B2 (en) 2019-08-23 2025-06-03 Rtx Corporation Slurry based diffusion coatings for blade under platform of internally-cooled components and process therefor

Also Published As

Publication number Publication date
DE1521269A1 (en) 1969-10-09
BE672291A (en) 1966-03-16
GB1100176A (en) 1968-01-24
DE1521269B2 (en) 1976-01-02

Similar Documents

Publication Publication Date Title
US3415672A (en) Method of co-depositing titanium and aluminum on surfaces of nickel, iron and cobalt
US3873347A (en) Coating system for superalloys
US4070507A (en) Platinum-rhodium-containing high temperature alloy coating method
US5688607A (en) Platinum group silicide modified aluminide coated metal superalloy body
US3951642A (en) Metallic coating powder containing Al and Hf
US5843588A (en) Diffusion coating products
US4326011A (en) Hot corrosion resistant coatings
GB1558978A (en) Metallic coatings
US4501776A (en) Methods of forming a protective diffusion layer on nickel, cobalt and iron base alloys
EP0596099B1 (en) Multiplex aluminide-silicide coating
US3957454A (en) Coated article
US3640815A (en) Method for surface treatment of nickel and cobalt base alloys
DE2419145A1 (en) ITEM COVERED, MANUFACTURING PROCESS AND MATERIAL FOR THE COVER
GB1566179A (en) Superalloys and coatings
JPH0253520B2 (en)
US4024294A (en) Protective coatings for superalloys
US3904789A (en) Masking method for use in aluminizing selected portions of metal substrates
US4371570A (en) Hot corrosion resistant coatings
US3979534A (en) Protective coatings for dispersion strengthened nickel-chromium/alloys
EP0131536B1 (en) Chromium boron surfaced nickel-iron base alloys
US4084025A (en) Process of applying protective aluminum coatings for non-super-strength nickel-chromium alloys
EP1076109A1 (en) Aluminiding of a metallic surface using an aluminum-modified maskant, and aluminum-modified maskant
US3996021A (en) Metallic coated article with improved resistance to high temperature environmental conditions
US6620518B2 (en) Vapor phase co-deposition coating for superalloy applications
US3953193A (en) Coating powder mixture