US3276865A - High temperature cobalt-base alloy - Google Patents

Description

United States Patent HIGH TEMPERATURE COBALT-BASE ALLOY John C. Freche, Fairview Park, Richard L. Ashbrook,

Cleveland, and Gary D. Sandrock, Fairview Park, Ohio,

assignors to the United States of America as represented by the Administrator of the National Aeronautics and Space Administration No Drawing. Filed June 15, 1964, Ser. No. 375,401

4 Claims. (Cl. 75-170) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

The present invention relates to an improved cobalt base alloy having high strength at elevated temperatures up to 2200 F. The invention is further concerned with a cobalt-base alloy that is resistant both to corrosion by liquid metals and to sublimation in a vacuum environment.

Various components of turboelectric space power systems, especially the ducting for the liquid metal heat transfer media, present diflicult material problems because they are subjected to the dual environment of liquid metals on one surface and a high vacuum on the other. Also, materials for these components must be workable and weldab'le to permit forming into sheet or tubing for ducting applications. Commercially available materials considered for such applications are certain stainless steels as Well aswrou-ght nickeland cobalt-base alloys. Refractory metal alloys of columbium have been considered for temperatures of 2000 F. and above.

Turbine engine parts and other engineering structures which operate in air at high temperatures must have adequate oxidation resistance or be capable of operating satisfactorily with protective coatings. Both cobaltand nickel-base alloys have been proposed for such structures.

Each of the classes of commercially available material considered for turbo-electric space .power systems has certain limitations. For example, stainless steels are restricted to applications where the temperature does not exceed approximately 1400 F. if long life in the neighborhood of 10,000 hours is to be obtained, even at the relatively low stress levels, such as 5,000 p.s.i., which are likely to be encountered in ducting applications. Wrought commercial cobaltand nickel base alloys are limited to applications where the temperatures do not exceed approximately l600 and 1700 F., respectively, at similar stress levels.

The vapor pressures of various metals differ, and this imposes another limitation on the use of certain commercially available materials. As a result of these differences in vapor pressures some metals tend to evaporate more than others in a high vacuum. Chromium and aluminum are particularly susceptible to evaporation losses. Virtually all stainless steels as well as cobaltand nickel-base alloys contain appreciable quantities of chromium, and most nickel-base superalloys contain aluminum, as well. Therefore, evaporation of chromium and aluminum may occur during long time exposure of these alloys to a high vacuum environment, and the structural integrity of these alloys may be atfected. The manner in which the alloying element is tied up in the metal matrix can greatly affect this process. It would be expected that a reduction in the percent of high vapor pressure alloying elements in the alloys used would lessen this problem.

From a corrosion resistance standpoint, cobalt resists corrosion by mercury more than nickel but less than iron. It appears that cobalt is at least equivalent to nickel in corrosion resistance in alkali metals up to the limit of its useful temperature range. Certain stainless steels, although acceptable up to 1600 F. in contact with the alkali metals, show a low compatibility with mercury if they have a high nickel and/ or a high chromium content. Nickel-base alloys are not compatible withmercury, but may be used with the alkali metals up to approximately 1700 F. Refractory columbium alloys, although having excellent elevated temperature strength characteristics and corrosion resistance to both mercury and the alkali metals, are very subject to oxidation. This makes pilot or ground tests of prototype units using this material extremely difficult and expensive.

It is, therefore, an object of the present invention to provide an improved cobalt-base alloy havinghigh strength at temperatures up to 2200? F.

Another object of the inventionis to provide an improved cobalt-base alloy which is resistant both to corrosion by liquid metals and to sublimation in a vacuum environment.

A further object of the invention is to provide an improved cobalt-base alloy which is workable and weldable to permit forming into sheet or tubing for ducting applications.

These and other advantages of the invention will be apparent from the specification which follows.

The present invention is embodied in alloys having the following composition range wherein the percentages are by weight: a I

Cobalt From about 36% to about 89.4%.

Tungsten From about 10% to about 45% Titanium From about .5 to about 2% Carbon From about '.1% to about 1% Zirconium From about 0% to about 3 Chromium From about 0%'to about 10%.

Rhenium From about 0% to about 3 The above alloy composition represents an improvement over the alloy disclosed in copending United States patent application Serial No. 355,126, filed March 26, 1964. The present alloys include chromium and rhenium in addition to the alloying constituents disclosed in the copending application.

Chromium is included because it is one of the most effective elements for strengthening the binary alloy Co-ZSW. The presence of chromium in relatively small chromium added to the alloy disclosed in the copending application has the following composition:

Percent Cobalt About 69.6 Tungsten About 25 Titanium About 1 Zirconium About 1 Chromium About 3 Carbon About .4

A comparison of as-cast stress-rupture properties of the present alloy with those of a preferred alloy disclosed in the copending application is shown in Table I wherein the samples are uncoated and nominal compositions are listed.

TABLE 1 Average Alloy Stress, Temp, Rupture p.s.i. F. Life in Air, hrs.

Co-25W-1Ti-1Zr-0AC 15,000 1,850 92 Co-25W-1Ti-1Zr-3Cr-0.4C 15, 000 1, 850 131 Rhenium is added to the above alloy because it is a potential solid-solution strengthener and stable carbide former. The evaporative loss rate of rhenium is extremely low, and another preferred alloy having rhenium added to the above preferred alloy has the following nominal composition:

Percent Cobalt About 67.6 Tungsten About 25 Titanium About 1 Zirconium About 1 Chromium About 3 Rhenium About 2 Carbon About .4

Uncoated samples having one of the preferred nominal compositions, Co-25W-1Ti-1Zr-3Cr-2Re-0AC, were stressrupture tested in air :at various conditions. The resulting data are summarized in Table II below. The 15,000 p.s.i., 1850 F. data are directly comparable to the data of Table I and show further improvement in stress rupture life over the alloys listed therein. Also shown are data for several of the strongest known commercially available cobalt-base alloys.

The short-time high temperature strength of the aforementioned preferred alloys is shown in Table III wherein ultimate tensile strengths of both preferred alloys as-cast and in sheet form are given for various temperatures. The ultimate tensile strength of a preferred alloy of the copending application at room temperature is presente for comparison purposes.

TABLE III Average Temp., Ultimate Alloy F. Tensile Strength,

p.s.i.

Co-25W-1Ti-1Zr-0AO (As Cast) Room 98, 580 Go-25W-1Ti-1Zr-3Cr-0AC (As Cast) Room 96, 425 Co-25W-1Ti-1Zr-3Cr-0.4G (As Cast)" 1, 645 63,000 Co-25W-1Ti-1Zr-3Cr-0.4C (As Cast) 1,800 37, 400 Co-25W-1Ti-1Zr-3Cr-0.4C (As Cast) 2, 000 24,000 C0-25W-1Ti-1Zr-3Cr-O.4C (As Cast) 2, 045 21, 800 Co-25W-1Ti-lZr-3Gr-0.4C (AS Cast 2, 20, 800 Co-25W-1Ti-1Zr-3Cr-2Re-OAC (As Cast) Room 98,050 Co-25W-1Ti-1Zr-3Cr-2Re-0AC (As Cast) 1, 600 73, 500 Oo-25W-1Ti-1Zr-3Cr-2Be-0.4C (As Cast) 1, 645 57,600 Co-25W-1Ti-1Zr-3Cr-2Re-0.4C (As Cast).-- 1,800 35, 700 C0-25W-1Ti-1Zr-3Cr-QRe-OAC (As Cast) 2, 000 25,300 Co-25W-1Tl-1Zr-30r-JRe-OAC (As Cast) 2, 045 24, 100 C0-25W-1Ti-1Zr-3 Cr-2Re-0.4C (As Cast) 2, 100 19, 650

SHEET ALLOYS Go-25W-1Ti-1Zr-0AC (As rolled) Room 179, 330 Co-25W-1Ti-1Zr-3Cr-0AG (As rolled) Room 221, 330 Go-25W-1Ti-1Zr-3Cr-0AC (Annealed)- Room 173, 750 Co-25W-1Ti-1Zr-30r-0AC (Annealed) 1, 600 71, H0 Co-25W-1Ti-1Zr-3Cr-0.4C (Annealed 1,800 37, 100 Co-25W-1Ti-lZr-3Cr-2Re-0AC (As rolled Room 211,150 Co-25W-1'1i-1Zr-3Cr-2Re-0AC (Annealed)- Room 181, 750 Co-25W-1Ti-1Zr-3Cr-2Re-0.4C (Annealed) 1,600 77,650 Co-25W-1Ti-1Zr-3Cr-ZRe-OAC (Annealed) 1,800 37,200

The cobalt-base alloys of the present invention can be prepared either by vacuum induction melting or by induction melting under an inert gas blanket. In inert gas melting the bottom of a cold zirconia crucible is covered with a small quantity .of electrolytic cobalt. Carbon in the form of lamp black compacts is placed in the crucible and covered with briquetted titanium, and the whole is covered with electrolytic cobalt nearly filling the crucible. A cylindrical shield is placed around the top of the crucible, and a flow of argon is directed at the top of. the charge.

Once the charge begins to settle, the remaining cobalt is added. When this portion of the charge is completely melted, tungsten is added in the form of short length rods. The melt is then superheated to 3050 F. and held ior three minutes to insure dissolving of the tungsten. The melt is then allowed to cool to 2900" F. and poured. During pouring the inert gas coverage is removed. Melts are poured into investment molds heated to 1600 F. and permitted to cool to room temperature naturally without speeding up the process artificially.

Alloys of this series have also been prepared by the more complex technique of vacuum melting in order that the etfectiveness as alloying constituents of such elements as titanium and zirconium should not be reduced by their reaction with atmospheric gases. This melting technique can result in further improvement in the properties. Improved cleanliness of the resulting vacuum melt can also result in better strength as well as improved ductility. Thus, by introducing a higher degree of complexity in the casting process, improved alloys can be obtained. Examples of rupture data from vacuum melts for two alloys are shown in Table IV.

The alloys of this invention derive their high elevated temperature strength from several mechanisms which can include solid solution strengthening of the cobalt matrix by tungsten, chromium and rhenium, by the precipitation of the intermetallic WCo phase and by the formation of various carbides of Ti, Zr, Cr, W and Re.

In an alternate embodiment of the invention this alloy series can readily be produced in either a cast or wrought form. These alloys have excellent characteristics for investment casting; yet, chill cast slabs can be hot rolled without prior working to thin strip with almost no edge cracking. Thin sheet sections of these alloys are readily weldable using electron beam welding procedures, an important requirement for ducting components.

What is claimed is:

1. A cobalt-base alloy capable of high load carrying capacity at elevated temperatures consisting essentially of from 39% to 89.4% cobalt, from 10% to 45% tungsten, from 0.5% to 2% titanium, from 0.1% to 1% carbon, from 0% to 3% zirconium, and from 0% to 10% chromium.

2. The cobalt-base alloy of claim 1 additionally containing up to 3% rhenium, the cobalt content of said alloy being adjusted to accommodate the addition.

References Cited by the Examiner UNITED STATES PATENTS 2,996,379 8/1961 Faulkner 75171 3,085,005 4/1963 Michael et a1. 75171 3,118,763 1/1964 Thielemann 75-170 3,223,522 12/1965 Rausch et a1 75171 DAVID L. RECK, Primary Examiner.

R. O. DEAN, Assistant Examiner.

Claims (1)

1. A COBALT-BASE ALLOY CAPABLE OF HIGH LOAD CARRYING CAPACITY AT ELEVATED TEMPERATURE CONSISTING ESSENTIALLY OF FROM 39% TO 89.4% COBALT, FROM 10% TO 45% TUNGSTEN, FROM 0.5% TO 2% TITANIUM, FROM 0.1% TO 1% CARBON, FROM 0% TO 3% ZIRCONIUM, AND FROM 0% TO 10% CHROMIUM.