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Publication numberUS3904382 A
Publication typeGrant
Publication dateSep 9, 1975
Filing dateJun 17, 1974
Priority dateJun 17, 1974
Also published asCA1038114A1, DE2526779A1
Publication numberUS 3904382 A, US 3904382A, US-A-3904382, US3904382 A, US3904382A
InventorsAdrian M Beltran, Norman R Lindblad, Gerald E Wasielewski
Original AssigneeGen Electric
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Corrosion-resistant coating for superalloys
US 3904382 A
An oxidation and hot corrosion resistant alloy for coating a superalloy substrate. The surface coating composition comprises a nickel base alloy containing chromium and silicon.
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Description  (OCR text may contain errors)

Elite ttes atent 11 1 Beltran et al. Sept. 9, 1975 [54] CORROSION-RESISTANT COATING FOR 3,155,491 11/1964 Hoppin ct al. 75 171 x 3,649,225 3/l972 Simmons 29/194 3,754,968 8/1973 Reznik 29 194 x [75] Inventors: Adri n M- B l r m- Lake; 3,810,754 Ford et al. 75 171 Norman R. Lindblad, Schenectady; Gerald E. Wasielewski, Rexford, all of N.Y.

Assignee: General Electric Company,

Schenectady, NY.

Filed: June 17, 1974 Appl. No.: 479,853

US. Cl 29/194; 75/134 F; 75/176 Int. Cl. B32B 15/04 Field of Search 29/194; 75/176, 171, 134 F References Cited UNITED STATES PATENTS l/ 1962 Stephenson 29/194 Primary ExaminerL. Dewayne Rutledge Assistant Examiner E. L. Weise Attorney, Agent, or Firm-John F. Ahern; James W. Mitchell 1 71 ABSTRACT An oxidation and hot corrosion resistant alloy for coating a superalloy substrate. The surface coating composition comprises a nickel base alloy containing chromium and silicon.

4 Claims, N0 Drawings CORROSION-RESISTANT COATING FOR SUPERALLOYS BACKGROUND OF THE INVENTION This invention relates to the coating of a superalloy substrate with an oxidation and hot-corrosion resistant surface coating alloy composition comprising a nickel base alloy containing chromium and silicon which alloy will be referred to hereinafter as AME-2.

Hot-corrosion resistance is required for applications in turbines burning natural gas or uncontaminated light distillates or in contaminated environments involving combusted diesel, heavy distillates or residual oils.

Many protective alloy coatings for superalloy substrates are shown by the prior art. These coatings include the conventional aluminide coatings which have technical limitations which restrict the coating thickness resulting in an early deterioration of the coatings and further do not exhibit the superior hot corrosion resistance properties of the subject alloy coating, especially in a hot-corrosion operating environment. The subject coating alloy is also more economical in its initial processing than the alloys of the prior art. The field repair of components removed from service is simple and more economical since selected areas can be recoated without need to mask or protect areas not requiring additional coating, as is the case of packaluminide or electron beam vapor deposited coatings.

In considering alloy coating compositions for superalloy substrates it was discovered that the alloy must exhibit the following characteristics:

1. Must be oxidation and hot-corrosion resistant over the temperature range l400 to about 2000F.

2. Must melt, wet and flow uniformly at some temperature below the incipient melting point of the superalloy substrate. Ideally, the vacuum brazing time/temperature cycle used to apply the coating alloy to the substrate should be compatible with the normal heat treatment cycle for the substrate.

3. Must be metallurgically stable, and compatible with the substrate alloy.

SUMMARY OF THE INVENTION It is therefore, an object of my invention to provide a superalloy with a coating alloy which is oxidation and hot-corrosion resistant over a temperature range.

Another object is to provide an alloy coating that melts, wets and flows uniformly at some temperature below the incipient melting point of the superalloy substrate.

A further object is to provide an alloy which is metallurgically compatible with the substrate alloy and may be applied as a thick coating.

Briefly stated, the present invention relates to a coating alloy for a superalloy substrate having the following composition: Chromium 4565%, Silicon 5-1 2%, Nickel-balance. All compositions are given in weight percent. A nominal coating composition as proposed by applicant may comprise 45% Chromium, Silicon with the balance Nickel.

It is known that high Cr levels are the most effective deterrent to hot corrosion caused by Na and S- bearing atmospheres in the temperature range 14001800F. At these temperatures, greater than about 36% Cr is required to generate a-Cr precipitate. However, it should be noted that the content of chromium should not be too high since the coating may become brittle over the range recited. The embrittlement is caused by the formation of excessive amounts of hard, body centered cubic a-Cr precipitate.

Similarly, silicon is beneficial for oxidation and hot corrosion resistance through the formation of SiO Silicon is used to control the melting and solidification behavior of the coating since the eutectic temperature in the pure Ni-Cr binary system occurs at 2450F which is too high for most nickel based superalloy substrates.

The coating may be applied to the substrate by various methods including vacuum brazing, which is an established industrial technique. However, other conventional methods of applying the coating alloy to the superalloy substrate could be used such as the slurry, aerosol spray or plasma spray plus heat treatment and transfer tape methods. However, some methods should be avoided such as the vapor deposition method which yields a coating microstructure oriented normal to the substrate surface, thus establishing potential shortcircuit diffusion paths e.g., grain boundaries, and growth defects for the introduction of corrodents such as sulphur and oxygen to the substrate. The resolidification structure of the subject vacuum brazed alloy is non-oriented, precluding this potential failure mode. Since the subject process involves the liquid and not the vapor state, greater segregation of the coating elements occurs. The present alloy takes advantage of this fact since the high chromium content produces a-Cr precipitate particles dispersed in y-solid solution nickel matrix containing a high chromium level. The lower melting point Ni1Si eutectic phase is equally well dispersed throughout the coating during solidification.

Those parts of the present invention which are considered to be new are set forth in detail in the claims appended hereto. The invention, however, may be better understood and the advantage appreciated from a detailed description as follows:

DETAILED DESCRIPTION A coating alloy was prepared using a nominal alloy composition comprised of 45% Chromium, 10% Silicon and the balance Nickel. Other compositions may be used falling within the range, supra. The substrate was prepared by mechanical abrading or by chemical cleaning plus electroplating a 0.2 to 1.0 mil layer of nickel thereon. The alloy used is in the form of a powder and is fabricated into a brazing transfer tape. The tape is comprised of 2OO +325 mesh powder, held together with about 5% of an organic binder on a plastic backing sheet. A template of the desired shape to fit the substrate is cut from the transfer tape. The plastic backing is removed and the tape applied to the substrate.

Additional liquid brazing cement may be needed to firmly adhere the tape in place. The coated part is then subjected to the vacuum brazing cycle. The vacuum brazing cycle is controlled to permit outgassing of the binder at about 700 to 1000F, to minimize contamination of the coating and substrate. The optimum vacuum brazing cycle consists of heating the alloy to a temperature of about 2075F for about 5 minutes followed by argon gas cooling. Generally no finishing treatments are required, since the as-brazed coated surface yields a surface finish in the 35 to 60 microinch (RMS) range. The part may receive a final heat treatment to develop the mechanical properties of the subtaining brittle intermetallic compounds, such as sigma and carbides.

The nominal alloy compositions of the superalloy substrates to which our coating is applied are listed in Table A as follows:

Table A Nominal Alloy Compositions of superalloy Substrates Alloy Ni Co Cr Al Ti Mo Cb Tu B Zr IN-738 Ba]. 8.5 16 3.4 3.4 1.75 2.6 0.9 1.75 0.01 0.04 0.1 1 lN-792 Hal. 9 12.5 3.5 4.1 1.9 4 (0.5 HT) 4 0.015 0.013 0.13 Rene '77 B111. 14 4.3 3.4 4.2 0.016 0.04 0.07 Rene '80 Ball. 95 14 3 0 5.0 4.0 4.0 N 0.015 0.03 0.17 MM-509 10 Ba]. 23.5 0.2 7 3.5 0.5 06

treatment sequence for the specific substrate alloy.

In the as-solidified condition, the microstructure of the subject alloy contains a mixture of 'y-Ni matrix, a-Cr precipitate particles, and NizSi eutectic. The precise composition and morphology of these phases depend both on the starting compositions of the subject alloy powder and substrate alloy, as well as the subsequent brazing and heat treatment cycles. The corrosion resistance of the subject alloy is derived from the high bulk Cr content (i.e. 45%) of the coating, but more specifically, it is due to the a-Cr particles and the high Cr, 'y-Ni matrix, which constitute a very significant portion of the coated structure. Since the coating is applied in the liquid state and resolidified, elements from the substrate are easily incorporated into the coating. Hence, the brazing cycle (time and temperature) can be utilized to control the morphology and composition of the coating to some extent. Nickel base superalloys have been coated in the temperature range 2060 to 2130F, with time-at-temperature between 2 and minutes. Lower brazing temperatures are not preferred due to AMB-2s melting characteristics. Higher brazing temperatures can be used depending upon the heating and cooling rates, the equipment used and other considerations. Specific superalloy substrates may even re quire higher temperatures; however, the optimum parameters for the reference alloys is 2075F for 5 minutes. In general, the higher the temperature, the shorter the time, to prevent excessive fiow, reaction, and interdiffusion with the substrate. High temperatures and/or longer brazing times promote large a-Cr particles, less NizSi eutectic but greater interdiffusion with the substrate. Lower temperatures and time produce smaller, better dispersed a-Cr particles and NizSi eutectic, with little substrate interdiffusion. One feature of the subject alloy coating in the as-coated condition is its lack of a complex diffusion zone between the coating and substrate. By contrast, conventional aluminide coatings are characterized by a finger-like diffusion zone con- The non-oriented structure of the subject alloy is due to the nature of the melting and re-solidification process. Segregation of the elements and resulting precipitates is related to composition, heat input during brazing, and cooling conditions. Line-of-sight vapordeposited coatings, such as the MCrAlYs deposited by electron beam evaporation, generally grow normal tothe substrate surface. Grain growth is, therefore, nor mal to the substrate, hence, growth defects are also oriented. Growth defects, when they occur in the subject alloy, are non-oriented solidification defects.

As previously stated, the subject alloy coating for a superalloy substrate has exhibited superior hot corrosion resistant properties over other prior art coated superalloys. Oxidation/hot-corrosion testing have been conducted under simulated gas turbine condition in a small combustion burner rig. A controlled atmosphere was produced by combusting doped diesel oil containing 1% S, to which artificial sea salt was mixed to produce 8 ppm Na in the combustion products. The rigs were run at I600F, at an air:fuel ratio of 60:1 with a gas velocity of 70 fps. The specimens were removed and air-blasted to room temperature every hours to simulate turbine shutdown and to promote oxide and- /or coating spallation under severe thermal cycling conditions. This is the most conditions test condition utilized to simulate a hot-corrosion operating environment.

In a first test AMB-2 was braze-coated on IN-738 using techniques previously described, and compared to available commercial aluminide coatings applied to IN-738. Results were obtained by sectioning the specimens, and metallographically determining at 100 times magnification the maximum depth of corrosion penetration through the coating and substrate, the average bulk coating surface loss, as well as an approximation of the area percent coating remaining. The results, listed in Table I below show the clear superiority of AME-2 over conventional aluminide coatings.

Table I Bulk Max. Surface S b tr te Penetration Loss, 7r. Coating Alloy Coating Fuel Temp. "F Time-Hr. Mils Mils Remaining IN-738 AME-2 D.O.+S.S. 1600 620 3.3 3.3

(HRT-Zl 1012 6.9 1.1 NA

(2)MDC1 307 6.5 0.5 0

Table I-Continued Bulk Max. Surface Substrate Penetration Loss, /r Coating Alloy Coating Fuel Temp. F Time-Hr. Mils Mils Remaining (3)MDC-9 635 4.5 1.6 60

I274 9.8 4.2 NA

NA-Not analyzed.

(l)RT2l-Niv;kel has: alloy ufChrum-alloy American Corp. contains l7-35'.( Al. 0l0 Cr, balance Ni and 5'71 of other incidental elements.

(I )MD('-I-Nick cl base allo of Howmct ('urp. contains l7-35Ci Al. balance nickel and up to 107: of other incidental elements. (3 )MDC LNickcl base alloy of Howmet Corp. contains 17-35); AI. 0-l0 Cr. billulice nickel and 5?! of other incidental elements.

It is important to note that the commercial process used for applying conventional aluminide coatings, known as pack concentration, has technical and economic limitations which restrict aluminide thickness to approximately 3 mils and somewhat less on Co-base superalloys. Since pack cementation is basically a vapor deposition process, applied thickness is timedependent. AME-2, however, can be applied up to about mils thickness, with no change in the time/- temperature vacuum brazing cycle. These data in Table I show that the aluminide coatings tested were essentially fully penetrated after just 600 to 1000 hours, with virtually no coating remaining. In many cases, significant corrosion of the IN-738 substrate resulted from the destruction of the coating.

The data in Table I further shows that a substantial portion of AME-2 remains after 2000 hours of testing.

This is due, in part, to the fact that AMB-2 can be applied in thicknesses up to about 10 mils, as stated above, with no change required in the technique or time/temperature parameters used in its application. Hence, AME-2 offers both a more corrosion resistant alloy composition and increased coating thickness, both of which result in a longer life.

Another series of burner rig tests were conducted on AMB 2 coated Rene-77, (See Table II below) and compared to conventional aluminide coatings. Some of the tests were run in an undoped natural gas atmosphere, which produces a normal oxidizing environture, or (2) the thermal treatment required to apply and stabilize the coating is incompatible with the substrates heat treatment, hence degrading its mechanical properties.

In Table III, standard 0.252 inch diameter as-cast test bars of Rene-77 and IN-738 were braze coated with AME-2, and tensile and rupture tested. The results are compared in Table III with aluminide-coated bars of these two alloys. Each coating/alloy combination was given the full heat treatment previously found optimal for that system. The data shows that the room temperature tensile properties of both IN-738 and Rene-77 are least affected by AME-2. Yield strengths are 10 to 15% higher than the aluminide coatings, with only slightly less ductility. The latter is due in part to the greater thickness of AMB-2.

Table II Mils Thickness Alloy Coating Substrate Coating Fuel Temp. F Time-Hr. Remaining Rene-77 AMB2 Diesel Oil Sea Salt I600 2483 3.3 MDC-I I600 [35 0 MDC-9 I 600 I 200 2.6 AMB-Z I800 31 4.5 MDC- I I800 600 1.2 MDC-9 I800 00 3.0 AME-2 Natural Gas I800 I I I0 4.2 MDC-l I800 I000 1.5 MDC-9 I 800 I000 3.0 AME-2 Natural Gas I900 I008 3.7 MDC-I I900 I000 1.5 MDC-9 I900 I000 3.0

Table 111 Mechanical Properties of Coated Alloys A) Tensile Properties (70F) Alloy Coating UTS-ksi 0.2 Y.S.. ksi 0.02 Y.S.. ksi 7! El /t RA Rene-77 None 136.5 1 12.0 105.5 9.0 12.4 AME-2 135.5 1 14.3 102.0 5.8 4.0 MDC-l 123.0 102.2 86.0 5.0 12.5 MDC9 1 17.0 101.0 87.0 4.0 8.6 lN-738 AME-2 142.5 121.0 105.0 4.3 6.3 MDC-l 146.2 1082 93.2 5.3 8.7 MDC-9 154.8 104.8 92.0 9.2 13.6 B) Stress Rupture Stress Temp. Time Alloy Coating ksi Hr. "/z El. /1 Ra P* lN-738 AMB-Z 15 1800 386.8 12.6 36.0 51.0 MDC-1 15 1800 215.9 25.4 32.2 50.5 MDC-9 15 1800 283.9 24.9 32.0 50.7 Rcne77 AME-2 15 1750 484.7 5.7 7.2 50.1

MDC-l 15 1800 235.3 5.4 10 6 50.6 MDC-9 1800 150.2 5.8 1 6 50.1

*Where P T log t) X 10" in stress-rupture at lXO0F/l5 ksi. AMBJ also produces superior results on 1N-738. For Rene-77. the parameter P shows that AMB-Z is at least equivalent to aluminide coating MDC-9. It is necessary to use the Larson-Miller parameter for comparison. since AMB-2 was tested at 2i different temperature.

What is claimed as new and desired to be secured by 2. The coating alloy of claim 1 consisting essentially Letters Patent 9 the Umted 'f 4. of 45% chromium 10% silicon and the'balance nickel. 1. An oxidation and corrosion resistant composite The alloy of Claim 1 wherein the microstructure comprising a superalloy substrate and a coating alloy Contains a mixture f 'y-Ni m trix, a-Cr precipitate parbonded thereto consisting essentially of the following tides and ;s eutectk;

l m si Weight Percenti 4. The coating alloy of claim 1 wherein the thickness Chr m 40-65% of the alloy coating composition for the superalloy may S111con 54 range up to 10 mils. Nickel Balance

Patent Citations
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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4369233 *Jul 19, 1979Jan 18, 1983Elbar B.V., Industrieterrien "Spikweien"Process to apply a protecting silicon containing coating on specimen produced from superalloys and product
US4743514 *Jun 29, 1983May 10, 1988Allied-Signal Inc.Oxidation resistant protective coating system for gas turbine components, and process for preparation of coated components
US4774149 *Mar 17, 1987Sep 27, 1988General Electric CompanyOxidation-and hot corrosion-resistant nickel-base alloy coatings and claddings for industrial and marine gas turbine hot section components and resulting composite articles
US5156321 *Aug 27, 1990Oct 20, 1992Liburdi Engineering LimitedPowder metallurgy repair technique
US5577655 *Nov 30, 1994Nov 26, 1996The Morgan Crucible Company PlcFlexible metal-containing tapes or films and associated adhesives
US6409795 *Nov 18, 1998Jun 25, 2002General Electric CompanyCoating methods, coating products and coated articles
US6416596Jul 29, 1994Jul 9, 2002The General Electric CompanyCast nickel-base alloy
US6428637Jun 7, 1995Aug 6, 2002General Electric CompanyMethod for producing large tear-free and crack-free nickel base superalloy gas turbine buckets
US6440238 *Aug 4, 2000Aug 27, 2002Alstom (Switzerland) LtdProcess for treating the surface of a component, made from a Ni based superalloy, to be coated
US6541075 *Feb 12, 2001Apr 1, 2003General Electric CompanyMethod for forming a thermal barrier coating system
US8070894Feb 11, 2004Dec 6, 2011The Nanosteel Company, Inc.Highly active liquid melts used to form coatings
US8262812 *Apr 4, 2007Sep 11, 2012General Electric CompanyProcess for forming a chromium diffusion portion and articles made therefrom
CN100427625CFeb 11, 2004Oct 22, 2008纳米钢公司Highly active liquid melts used to form coatings
EP0284793A2 *Mar 1, 1988Oct 5, 1988General Electric CompanyOxidation-and hot corrosion-resistant nickel-base alloy coatings and claddings for industrial and marine gas turbine hot section components and resulting composite articles
EP0381819A1 *Oct 13, 1989Aug 16, 1990Detlev Dr. RepenningTool for processing elastomeres
WO1992003241A1 *Aug 28, 1990Mar 1, 1992Liburdi EngineeringPowder metallurgy repair technique
WO2004072312A2 *Feb 11, 2004Aug 26, 2004Nanosteel CoHighly active liquid melts used to form coatings
U.S. Classification428/553, 428/680, 428/667, 428/926, 148/442, 420/588
International ClassificationB23K35/32, C23C30/00, C22C27/06, C22C19/05, B23K35/22, C23C10/54, F01D5/28, B23K35/30
Cooperative ClassificationB23K35/304, C22C27/06, C23C30/00, B23K35/32, Y10S428/926, C22C19/052
European ClassificationB23K35/32, B23K35/30F2, C22C27/06, C23C30/00, C22C19/05P2