US 4,078,951 AGrant
Method of Improving Fatigue Life of Cast Nickel Based Superalloys and Composition
Issue Date:1978-03-14
•16 Claims
Abstract
The invention consists of a method of producing a fine equiaxed grain structure (ASTM 2-4) in cast nickel-base superalloys which increases low cycle fatigue lives without detrimental effects on stress rupture properties to temperatures as high as 1800.degree. F. These superalloys are variations of the basic nickel-chromium matrix, hardened by gamma prime [Ni.sub.3 (Al, Ti)] but with optional additions of cobalt, tungsten, molybdenum, vanadium, columbium, tantalum, boron, zirconium, carbon and hafnium. The invention grain refines these alloys to ASTM 2 to 4 increasing low cycle fatigue life by a factor of 2 to 5 (i.e. life of 700 hours would be increased to 1400 to 3500 hours for a given stress) as a result of the addition of 0.01% to 0.2% of a member of the group consisting of boron, zirconium and mixtures thereof to aid heterogeneous nucleation. The alloy is vacuum melted and heated to 250.degree.-400.degree. F. above the melting temperature, cooled to partial solidification, thus resulting in said heterogeneous nucleation and fine grains, then reheated and cast at about 50.degree.-100.degree. F. of superheat. Additions of 0.1% boron and 0.1% zirconium (optional) are the preferred nucleating agents.
Metadata
Assignee
- University Patents, Inc.
Inventors
- Allen F. Denzine
- Thomas A. Kolakowski
- John F. Wallace
Application Information
Application Number:US 6723500
Filing Date:1976-03-31
Priority Date:1976-03-31
Art Unit:111
Classifications
IPC:
C22C 1905
Field of Search:
75148171;170;8232;32.5
Patent Drawings
This patent does not have any drawings.
Description
Example I -- 713 Lc
To obtain a fine equiaxed structure requires that nucleation occur at a large number of sites. Inoculation together with constitutional supercooling has been found to be the most effective technique for grain refinement, with Ti, Zr, B and C most widely used as inoculants and the solute elements present in the alloy. For the alloys under consideration, titanium and carbon contents are closely controlled to allow the formation of a suitable proportion of gamma prime and carbides for optimum mechanical properties, but sufficient latitude is available for additions of these elements as inoculants without major microstructural changes. Using an inoculated mold preheated to 1600.degree. F, additions of 0.1 wt. % Zr (in sponge form) and 0.1 wt. % B (elemental powder wrapped in nickel foil packets) were made to a crucible charged with 713 LC.
To obtain refinement, suitable substrates must be formed in the melt. From the Ti-B-C ternary phase, it is apparent that the melt must be heated in excess of 2730.degree. F. (1510.degree. C.) to form TiB and TiC, with melt temperatures in excess of 2804.degree. F. (1540.degree. C.) required to form TiB.sub.2. Based on this information, the maximum melt temperature was established as 2850.degree.-2900.degree. F. (1565.degree.-1594.degree. C.) After the maximum temperature is achieved, the charge is allowed to cool in the crucible until solidification has progressed sufficiently. The charge is then reheated and poured quickly with a 50.degree.-100.degree. F. (28.degree.-55.degree. C.) superheat.
This is a fine equiaxed structure with a grain size of ASTM No. 3. The same technique was then applied to the larger hub mold. This fine equiaxed structure (with a thin columnar region at the surface) has a grain size of ASTM No. 2.
Example Ii -- Mar-M 246
This technique was next applied to alloy MAR-M 246 hub and rim molds, using the same additions. The equiaxed grain sizes are ASTM No. 4 and ASTM No. 3.5 for the rim and hub sections, respectively. The additional refinement in this alloy compared to that of 713 LC is attributed to the higher carbon and refractory content of MAR-M 246.
Example Iii -- C 103
The application of the previously described technique proved unsuccessful with rim sections of alloy C 103. A coarse columnar structure was produced. In alloy C 103 the most significant alloying addition (compared to 713 LC and MAR-M 246) is 1% hafnium. Since the existing grain refinement theory is based on the formation of titanium and zirconium borides and carbides in the melt (which then act as substrates for heterogeneous nucleation), it is significant that a higher negative free energy of formation exists for hafnium borides and carbides than for the titanium and zirconium counterparts. The hafnium in the alloy would be expected to react preferentially with the boron and carbon, reducing the amount available to the titanium and zirconium. The hafnium borides and carbides apparently do not act as effective substrates for reasons that will be discussed later.
To verify the presence of hafnium as the source of the problem, a heat was made using alloy MAR-M 246 and a 1% addition of hafnium. The casting technique employed was that which previously produced refinement in MAR-M 246. The resulting macrostructure was a coarse equiaxed structure, with a region of fine columnar grains at the surface.
To overcome the influence of the hafnium, an addition of 1% calcium cyanamide (CaCn.sub.2) was made to provide nitrogen to tie up the hafnium and thereby free some carbon to react and form substrates. This technique, coupled with the elimination of the use of hot top (to allow melted off dendrites to "rain down" and act as nuclei) produced the refinement, i.e. a wholly equiaxed structure with an average grain diameter of 0.15 inch. While this technique produced promising results in terms of structure control, the CaCn.sub.2 addition formed a "slag" which bridged across the crucible, greatly hindering temperature measurement and pouring. Based on the work of Tarshis et al, [Tarshis, L. A., et al, "Experiments on the Solidification Structure of Alloy Castings", Metallurgical Transactions, September, 1971.] the effect of an addition of 1% cerium to C 103 was evaluated. An equiaxed structure with grain size slightly larger than that produced by CaCn.sub.2 additions was the result.
Since these other inoculants proved ineffective in producing a fine equiaxed structure in C 103, boron and zirconium additions were employed using a modified process. Two approaches to this problem were available:
1. Alter the hafnium borides and carbides to convert them to suitable substrates such as by the addition of an alloying element to precipitate on the hafnium compounds and alter their surface character.
2. Suppress the formation of the hafnium compounds while promoting the formation of titanium and zirconium borides and carbides.
The first alternative proved to be unsuccessful, but the second procedure provided refinement. A comparison of the Ti--ZR--B and the Ti--Hf--B ternary phase diagrams indicates that the titanium and zirconium borides begin to form upon cooling from temperatures above 2630.degree. F. (1432.degree. C.) while the hafnium borides can begin to form upon cooling from temperatures over 2760.degree. F. (1516.degree. C.). Therefore, heating to the intermediate temperature range between 2630.degree. F. and 2760.degree. F. could result in the formation of effective substrates with a minimal loss of substrates from the presence of hafnium.
Example Iv -- C 103
Using boron and zirconium as inoculants and a cobaltous oxide coated rim mold, a C 103 heat was made by heating to approximately 2660.degree. F. (1460.degree. C.) and then pouring with a 50.degree. F. (28.degree. l C.) superheat. The periphery is composed of fine columnar grains because of the action of the mold inoculant; the body of the casting is equiaxed with an average grain diameter of 0.07 inch. While this structure is not as fine grained as those of 713 LC or MAR-M 246, it represents a significant improvement over previous attempts with C 103.
A second heat was made under the same conditions with the maximum temperature increased to the upper limit (2760.degree. F.) specified by the phase diagrams. This macrostructure is wholly equiaxed, with an average grain diameter of 0.004 (ASTM No. 3.5). The same technique was then applied to an inoculated hub mold. Again, the structure is wholly equiaxed with an average grain diameter of 0.005 inch (ASTM No. 3).
For all three alloys, the minimum grain diameter for refined castings is very nearly equal to the secondary dendrite arm spacing of baseline castings. Further refinement of equiaxed grains can be obtained by varying the local solidification time, a technique which is used to refine secondary arm spacing of columnar castings. This results in a range of equiaxed grain sizes produced by variations in pouring temperature and mold preheat temperature.
Example v -- C 103
Further examples were completed using 0.01% to 0.2% by weight boron with comparable results in physical properties and grain size. Zirconium 0.01 to 0.2% by weight produced equivalent results.
Example Vi
In still another example 16 heats were run. All heats were run using MAR-M 246 because of the significant improvement in mechanical properties which this alloy exhibited upon grain refinement. Some of the heats were melted with one-half atmosphere of argon (inert gas) in the melt chamber, and others were melted in vacuum. Additions of 0.1% boron and/or zirconium were charged with remelt stock. Various combinations of thermal cycles and superheats (pour temperature) were tried in an effort to establish the most reliable and feasible method of grain refinement for use in a production facility. Because the experiments were conducted to find the limits of the process, only two heats were completely grain refined. In heat No. 3 argon was used with 0.1% boron, no zirconium, 50.degree. F. superheat for pouring, and the regular thermal cycle (2800.degree. F., freeze) to produce an equiaxed 0.004 inch grain size (ASTM No. 3.5).
In heat No. 10 argon was not used, but 0.1% boron, 100.degree. F. superheat pour produced an equiaxed 0.006 grain size. This was a production run. It was noted that heat No. 10 was grain refined without the one-half atmosphere of argon in the melt chamber. Attempts to grain refine in the laboratory without back filling with argon were unsuccessful; however, this was attributed to the relatively poor (30 micron) vacuum which the experimental furnace provided. This inferior vacuum increased the difficulty of introducing boron into the melt with the movement of gases over the melt. The very good vacuum (less than 1 micron) which was achieved on the production melting unit eliminated this problem. For this reason grain refinement can be realized in the production environment utilizing conventional vacuum melting procedures.
In other heats regardless of the vacuum, or use of argon, it was not possible to obtain the grain refinement sought. In some heats boron and/or zirconium were omitted and large grains resulted. In another 100.degree. F. to 200.degree. F. superheat pour, columnar structure and large grains resulted. The object learned is that low pouring temperature promoted grain refinement
Following the above, a set of heats was run as in the manner of No. 3 and No. 10 with zirconium and no boron which produced an equiaxed structure 0.0061 inch grain size. The other experimental conditions were as described, previously.
Example Vii
In a further test with MAR-M 246 a series of heats were cast using the technique employed previously. One heat was a control sample cast with normal production procedures. The remaining heats were cast with 0.1% boron by weight melted under vacuum (1 micron). These alloys were melted at +300.degree. F. superheat for the control, and each sample was run at a different superheat temperature, namely, +400.degree., +400.degree., +400.degree., +450.degree. F., and +375.degree. F., respectively. They were poured at +300.degree. F. for the control and +10.degree. F., +25.degree. F., 15.degree. F., +15.degree. F., and +25.degree. F. for the five samples. All samples produced equiaxed grains 0.004 inch in size, whereas the control was columnar and 0.250 inch in grain size. Because of mold filling problems, it was concluded that it is advantageous to use slightly higher pouring temperatures such as +50.degree. F. superheat. Mechanical testing confirmed the earlier results.
Microstructural Analysis
Considerable variation exists on the microstructure from alloy to alloy as well as for a particular alloy in the refined and non-refined condition. A microstructural analysis was performed on the previously discussed castings to describe and compare the carbide morphology, grain boundary structure and gamma prime size and distribution. The grain boundaries are smooth and rounded, connected by the characteristic "Chinese script" carbide morphology. The gamma prime phase is more prominent, occupying a volume fraction of between 60-70%. Two types of carbides are present, the large, blocky MC carbides and the angular, elongated M.sub.23 C.sub.6 occupying a portion of the grain boundaries. This structure is unchanged with the addition of the cobaltous oxide mold prime coat.
Using the grain refinement technique discussed previously (B plus Zr additions) results in a modification of the carbide morphology from a script type to a cellular type. While this cellular carbide morphology is generally regarded as being detrimental to ductility, the extent of damage to properties is strongly dependent on the amount of grain boundary gamma prime which surrounds the carbides. A "skeletal" phase identified as a boride is also present in the refined microstructure.
MAR-M 246 in the refined condition shows both cellular and script carbide morphology with a higher volume fraction of MC carbides compared to 713 LC because of the higher carbon and refractory content in this alloy. Grain boundaries are smooth and angular, and the gamma prime volume fraction is comparable to that of 713 LC.
In micrographs of a baseline heat of alloy C 103, there is a marked change in the gamma prime phase with the appearance of circular islands of gamma/gamma prime eutectic. While some script type carbides remain in the grain boundaries, the grains are populated with large angular (hexagonal) carbides. Micrographs of this alloy in the "refined" condition (CaCn.sub.2 addition) show the convoluted grain boundary geometry resulting from the presence of the gamma/gamma prime eutectic islands. The grain boundary carbides have assumed a cellular morphology as experienced with the other alloys following refinement. These have a typical island surrounded by celluar carbides and skeletal borides. The pronounced microstructural changes (convoluted grain boundary geometry; large, angular MC carbides; gamma/gamma prime eutectic) are the result of the 1% hafnium present in the alloy. This was confirmed by the addition of 1% hafnium to MAR-M 246.
The microstructure of C 103 has undergone considerable change during grain refinement. Most significant is the increase in the volume fraction in the gamma/gamma prime eutectic with a decrease in the number and size of the angular carbides within the grains. The microstructure of a rim section of C 103 inoculated with CaCn.sub.2 produced an average grain diameter of 0.15inch. A rim section heated to 2660.degree. F. (1460.degree. C.) resulted in an average grain diameter of 0.005 inch. A rim heated to 2760.degree. F. resulted in an average grain diameter of 0.004 inch. With an increase in gamma/gamma prime eutectic there was a decrease in grain size. Since the gamma/gamma prime eutectic forms upon the addition of hafnium, and based upon the theory that the formation of hafnium carbides and borides retards grain refinement, it follows that by preventing the formation of the hafnium compounds, a greater amount of hafnium is available for the formation of the gamma/gamma prime eutectic phase.
Microprobe Analysis
An electron microprobe analysis was performed on grain refined rim sections of the three alloys to investigate the partitioning of the major alloying elements.
In alloy 713 LC, the carbides are denuded of nickel with titanium-rich MC carbides and chromium and molybdenum-rich M.sub.23 C.sub.6 carbides as predicted by the equation:
Little information was gained on the partitioning of Ta and Zr or B. Aluminum is uniformly distributed in the gamma prime.
A similar result is present for alloy MAR-M 246, with carbides lean in terms of Ni and Co and Ta, Zr, and Ti partitioned to the MC carbides. The M.sub.23 C.sub.6 carbides are rich in Cr, Mo, and W. Little information is available on C and B which are present in small concentrations and as light elements are difficult to detect. The Al is uniformly distributed in the gamma prime.
In alloy C 103, the hafnium is partitioned in two important locations. Higher concentrations of Hf are present in the gamma/gamma prime eutectic phase compared to the matrix. This element is also concentrated in the angular primary carbides characteristic of hafnium-modified alloys. Two types of primary carbides form; one of these is hafnium rich, the other Ti rich in the form:
within the primary carbides the Hf tends to accumulate at the periphery with Ti at the center. This tendency was confirmed by measuring hafnium and titanium counts per second while traversing a carbide at high magnification. At the carbide periphery, hafnium counts are increased by a factor of 3 or 4 compared to the center of the carbide. The reverse is true for titanium with counts per second decreasing by a factor of 2 or 3 from the center to the edge of the carbide.
The discrete nature of the hafnium-rich carbides (as opposed to a script morphology) suggests that these carbides form early in the solidification process, consuming much of the available carbon. This change in the solidifcation sequence would occur if hafnium depressed liquidus and solidus temperatures of the alloys; this circumstance has been observed.
These results provide a clue regarding the difficulty of grain refining the hafnium-modified alloys. Based on the assumption that the formation of carbides and borides in the melt results in stable substrates for nucleation, a smooth angular carbide could fail to act as an effective substrate since the "surface roughness" criterion would not be met. Further, a poor match occurs between the crystal structure of the parent solid and the inoculating particle. The lattice parameter of HfC (4.64A) is considerably larger (32%) than that of the nickel matrix (3.52 A).
All three alloys are generally insensitive to increasing test temperature in terms of yield strength and tensile strength. For baseline heats, the yield strength increases from about 110ksi for 713 LC to 125ksi for MAR-M 246 and 130ksi for C 103. Grain refinement results in an increase in yield strength for 713 LC (120ksi) and MAR-M 246 (135ksi) with a slight decrease in tensile strength for these alloys. Both the yield (128ksi) and tensile strengths of C 103 decrease following grain refinement. Columnar grained castings show reduced tensile and yield strengths in comparison to their baseline and refine counterparts. This tensile data falls within the band established for cast nickel-base superalloys, as shown in a plot of yield strength versus temperature and tensile strength versus temperature.
At temperatures above 1200.degree. F., all three alloys undergo a decrease in ductility. This characteristic feature of nickel-base superalloys is significant. Alloy 713 LC has considerably greater ductility (12% elongation) than MAR-M 246 (5%) and C 103 (6%) in both the baseline and refined states because of the relatively small volume fraction of carbides in this low carbon alloy. Grain refinement produces a decrease in ductility for a given alloy and test temperature. This can be attributed to the increase in brittle constituents (such as skeletal networks of borides and altered carbide morphologies) which form during refinement. The columnar grained castings have ductility values greater than refined castings but less than baseline castings. This is the result of the alignment of the columnar grain boundaries normal to the major stress axis, reducing ductility compared to baseline castings without the presence of the boride and altered carbide networks.
Observations of Fatigue Tests
1. The baseline material shows considerably greater scatter than the refined material because of the anisotropy effects. An accurate assessment of the limits of the scatter band requires testing a much greater number of specimens. The limits of the scatter band are essential to designers who intend to use the lower limit in the design of a rotor.
2. For alloys 713 LC and MAR-M 246, the slopes of the fatigue curves follow the relation:
with K varying from 0.032 for 713 LC columnar to 0.07 for MAR-M 246 refined and X = 0.24. Alloy C 103 has a considerably shallower slope and does not conform to this behavior.
3. The performance of baseline MAR-M 246 and baseline 713 LC is nearly identical. Columnar grained MAR-M 246 has a distinct advantage over columnar 713 LC. 4. The fatigue performance of refined 713 LC and MAR-M 246 is superior to their respective columnar or baseline grain structures. At a strain amplitude of 0.003, refined MAR-M 246 has a factor of four increase in cycles to failure compared to baseline MAR-M 246. Refined 713 LC has fatigue life increased 2 times that of baseline 713 LC at the same strain amplitude.
5. The shallow slope of the 3 strain-life curves for C 103 indicates that this alloy is extremely sensitive to small changes in strain amplitude. This alloy is also insensitive to changes in grain morphology, with columnar, baseline and refined data falling on nearly the same line.
The poor strength behavior of the columnar grained alloy in room temperature fatigue and room and elevated temperature tensile tests predicates the elimination of this grain morphology in future testing. Emphasis is, therefore, focused on the performance of baseline and refined material.
At 1000.degree. F., the elongation of 713 LC baseline has decreased from 15% to 12%, with MAR-M 246 baseline dropping from 8.7% to 5.0%. Refined 713 LC, refined MAR-M 246 and C 103 baseline and refined show a much smaller decrease in ductility over the same temperature range. The mechanism by which this decrease in ductility affects the slope of the fatigue curve can be explained in terms of the elastic and plastic strain contributions to the total strain life-curve. At low strain amplitudes the fatigue performance is dependent mainly upon the strength of the material since the straining is almost totally elastic. At higher strain amplitudes, the dominance of the elastic factor is reduced as the amount of plastic straining increases. The importance of material ductility, as reflected by the fatigue ductility exponent and coefficient, increases with increasing plastic strain. Therefore, the reduced ductility present at 1000.degree. F. results in decreased high strain fatigue life with low strain fatigue lift unaffected, thereby reducing the slope of the fatigue curve.
The fatigue curves for rim material tested at 1400.degree. F. (760.degree. C.) have the following significant features:
1. The performance of refined MAR-M 246 and refined 713 LC is superior to that of baseline heats of those materials.
2. The slopes of all six fatigue curves are reduced compared to the 1000.degree. F. data. This is again the result of a ductility loss, with the minimum in the ductility versus temperature occurring at 1400.degree. F. The reduced slopes have the parameters X = 0.20 for 713 LC and X = 0.18 for MAR-M 246.
3. At high strain amplitudes, 713 LC has considerably better fatigue life than MAR-M 246 or C-103. This is attributed to the ductility of 713 LC which, at 1400.degree. F., is three times of MAR-M 246 or C 103. At lower temperatures 713 LC had nearly double the ductility of MAR-M 246, but the strength advantage of MAR-M 246 was sufficient to compensate for its inferior ductility.
4. At low strain levels MAR-M 246 has the superior fatigue life. Since the straining is elastic in this region, the strength of MAR-M 246 dominates.
5. At low strain levels, the fatigue life of MAR-M 246 and C 103 is superior (at 1400.degree. F.) to that at room temperature. At 1400.degree. F., the decrease in the modulus of elasticity results in less stress required to achieve a given strain. Since the fatigue test is being conducted in a strain control mode, specimens at the same strain level are subject to less stress at 1400.degree. F. than at room temperature. While the modulus decreases with temperature, the yield strengths of these alloys are essentially constant up to 1400.degree. F. Therefore, under wholly elastic strain conditions, fatigue life at 1400.degree. F. will be superior to that at room temperature.
For MAR-M 246 and 713 LC, refined specimens have superior fatigue performance compared to their base-line counterparts. The fatigue parameters for room temperature hub mold specimens are X = 0.24 and K = 0.072 for MAR-M 246 refined and K = 0.051 for 713 LC baseline. Again, C 103 has a much shallower slope of the .DELTA..epsilon..sub.T /2 vs, 2N.sub.f curve than 713 LC or MAR-M246.
The 500.degree. F. fatigue performance of hub mold material shows at this low test temperature the fatigue curves are nearly identical to those at room temperature. This is the expected result since there are no significant changes in tensile properties at 500.degree. F. compared to room temperature.
The fatigue curves for each of the alloys at various test temperatures and grain morphologies show for 713 LC the decrease in slope of the fatigue curves with increasing test temperature, which is apparent for both baseline and refined materials. Baseline material is more susceptile to the slope change as it experiences a greater decrease in ductility with increasing temperature.
The behavior of MAR-M 246 is significantly different as the slopes of the fatigue curves decrease with increasing temperature. However, the baseline and refined curves, at a given temperature, remain nearly parallel. The high temperature, low strain behavior of MAR-M 246 is interesting since the reversals to failure exceed those for room temperature specimens at the same strain amplitude.
C103 has the unique characteristic of being insensitive to changes in test temperature or grain morphology with extreme sensitivity to changes in strain amplitude. At low strain amplitudes this material is comparable to the other alloys in terms of fatigue life, but at strain amplitudes in excess of 0.004 inch/ it is decidedly inferior.
With respect to the foregoing specification, it is important to state that MAR-M 246 is a trademark for a Martin Marietta Corporation alloy; INCO 713 LC or 713 LC is a trademark for an International Nickel Company alloy; and C 103 is a trademark for an Allison Division of General Motors Company alloy.
Summary and Conclusions
The subject invention concerns the influence of grain refinement and microstructural control on the significant properties of nickel-base superalloys for use in integrally cast turbine rotors and other super-alloy applications. The alloys testes were 713 LC, MAR-M 246 and C 103, and the properties investigated were tensile (room temperature to 1400.degree. F.), mechanical fatigue (room temperature to 1400.degree. F.), thermal fatigue, hot corrosion, and stress rupture.
1. The present invention consists of a gain refinement technique in which:
a. An alloying addition of 0.1% B and optionally 0.1% Zr is made.
b. Melting in a vacuum furnace or back filling the chamber with one-half atmosphere of argon to prevent the loss of said alloying additions.
c. For 713 LC and MAR-M 246 the melt must be raised to temperatures in excess of 2800.degree. F., i.e. 350.degree. F. superheat, before cooling to insure the formation of proper nucleation substrates. For C 103, the maximum temperature must be between 2630.degree. F. and 2760.degree. F, i.e. 300.degree. F. superheat.
d. Cooling until partial solidification has occurred.
e. Reheating and pouring with approximately 50.degree.-100.degree. F. superheat.
f. Refinement is attributed to the formation of titanium and/or zirconium borides which act as stable substrates for nucleation.
2. Tensile Test Results:
a. Coarse grained samples showed considerable anisotropy.
b. Grain refinement produced an increase of 10ksi in the yield strength of 713 LC and MAR-M 246 with a slight decrease in tensile strength. Both the yield and tensile strengths of C 103 decrease following grain refinement. Grain refinement also produces a decrease in ductility for a given alloy and test temperature.
3. Low-cycle mechanical fatigue results:
a. Grain refinement produces an increase in fatigue life by a factor of 2-4, i.e. the base alloy lasted 700 hours and this new alloy 1500 to 3000 hours.
b. As the test temperature increases, the slopes of the strain life curves decrease due to the ductility loss at elevated temperatures. At low strain amplitudes, fatigue life increases with increasing temperature.
c. The fatigue performance of C 103 is insensitive to changes in test temperature and grain morphology, but it is extremely sensitive to strain amplitude.
4. Thermal fatigue test results:
a. Burner rig testing failed to produce thermal fatigue cracks in baseline or refined specimens of the three test alloys.
b. The corrosion rate (as measured by weight change) was increased for grain refined samples.
c. The corrosion rate of C 103 (baseline and refined) was significantly greater than that for the other alloys.
d. The increased corrosion rate of C 103 was attributed to the insufficient aluminum content in this alloy.
5. Fatigue failure mechanisms:
a. Inclusions, microshrinkage and precracked carbides at the specimen surface act as stress raisers to promote microcrack formation.
b. Microcracks propagate slowly as they link up with each other and with discontinuities such as cracked carbides or microshrinkage.
c. Catastrophic crack propagation results when the critical crack length is attained (for a given geometry, material and test conditions).
6. Commercial significance of results:
a. Based on the results of a series of preliminary tests, it was verified that the structure control techniques developed can be applied in a production environment.
b. Either 713 LC or MAR-M 246 in the grain refined condition are preferred for use in integrally cast turbine rotors. These alloys offer a definite improvement in low-cycle fatigue properties without a sacrifice in castability or cost, and are most easily adapted to current production equipment.
c. C 103 is less suitable for use in the rotor application tested.
The invention has been described with reference to the preferred embodiment. Obviously, modifications and alterations will occur to others upon the reading and understanding of the specification. It is our intention to include all such modifications and alterations insofar as they come within the scope of the appended claims or equivalents thereof.
Claims
What is claimed is:
1. A method for producing heterogeneous nuclei in test nickel-base superalloys which results in the grain refinement of said superalloys and in the improvement of the low cycle fatigue properties in said superalloys while mantaining the present stress rupture properties of said superalloys, comprising: charging a nickel-base superalloy in a crucible; adding to said superalloy from 0.01 to 0.20 percent of a member selected from the group consisting of boron, zirconium and mixtures thereof for causing the formation of a substrate for heterogeneous nucleation; melting said charged nickel-base superalloy and said selected member in a vacuum furnace; superheating said charged nickel-base superalloy and said selected member to a temperature of about 250.degree. F. to about 400.degree. F. above said melting temperature in a period of about two minutes to about eight minutes to form heterogeneous nuclei in said nickel-base superalloy; and cooling until partial solidification, reheating and pouring said superalloy with about 50.degree. F. to about 100.degree. F. of superheat, whereby an equiaxed fine grain structure results in said superalloy.
2. The method as described in claim 1 wherein said nickel-base superalloy is: carbon; 0.02 - 0.35 chromium; 6.0 - 17.0 molybdenum; 2.5 columbium, Tantalum; 0.25 - 3.0 aluminum; 2.0 - 8.0 titanium; 0.1 - 3.0 boron; 0.001 - .2 zirconium; 0.001 - .5 cobalt; 2.0 - 15.0 tungsten; 5.0 - 20.0 nickel; Balance plus impurities as low as possible.
3. The method as described in claim 1 wherein said nickel-base superalloy is: carbon; 0.03 - 0.07 chronium; 11.0 - 13.0 molybdenum; 3.8 - 5.20 columbium, tantalum; 1.50 - 2.50 aluminum; 5.50 - 6.50 titanium; 0.40 - 1.00 boron; 0.005 - 0.015 zirconium; 0.05 - 0.15 nickel; Balance plus impurities as low as possible.
4. The method as described in claim 1 wherein said nickel-base superalloy is: carbon; 0.14 - 0.18 chromium; 11.2 - 11.8 molybdenum; 1.75 - 2.25 columbium, tantalum; 4.80 - 5.20 aluminum; 3.30 - 3.70 titanium; 3.80 - 4.20 boron; 0.010 - 0.020 zirconium; 0.05 - 0.12 cobalt; 8.0 - 9.0 tungsten; 4.8 - 5.2 hafnium; 0.80 - 1.202 nickel; Balance plus impurities as low as possible.
5. The method as described in claim 1 wherein said casting takes place in an inert atmosphere.
6. The method as described in claim 1 wherein said added selected member is 0.1 percent boron.
7. The method as described in claim 1 wherein said added selected member is a combination of 0.1 percent boron and 0.1 percent zirconium.
8. A method of grain refining cast nickel-base superalloys which comprises: combining said superalloy with 0.01 percent to 0.20 percent of a member selected from the group consisting of boron, zirconium and mixtures thereof; melting said superalloy and said selected member in a furnace; superheating said superalloy and said selected member to a temperature of about 250.degree. to about 400.degree. F. above said melting temperature in a period of about 2 minutes to about 8 minutes; and cooling until partial solidification, reheating and pouring said superalloy with about 50.degree. F. to about 100.degree. F. superheat, whereby an equiaxed fine grain structure results in said superalloy.
9. The method of claim 8 in which said furnace is a vacuum furnace.
10. The method of claim 8 in which an inert atmosphere is used in said furnace.
11. The method of claim 8 in which said selected member is 0.1 percent boron.
12. The method of claim 8 in which said selected member is a combination of 0.1 percent boron and 0.1 percent zirconium.
13. A new, improved cast nickel-base superalloy consisting essentially of the following approximate composition: Carbon; 0.02 - 0.17 Chromium; 6.0 - 20.0 Cobalt; 2.0 - 15.0 Molybdenum; 1.7 - 6.0 Tungsten (W); 2.5 - 20.0 Columbium, Tantalum; 0.9 - 6.5 Iron; 0 - 4.5 Titanium; 0.1 - 4.7 Aluminum; 2.0 - 8.0 Boron; 0.001 - 0.20 Zirconium; 0.001 - 0.50 Nickel; Balance plus impurities as low as possible, the improvement of which consists of a grain refining agent having 0.01 percent to 0.20 percent selected from the group consisting of boron, zirconium and mixtures thereof, and further being characterized by a fine equiaxed grain structure with an ASTM grain size of two or finer and by improved fatigue life at both room and elevated temperatures (1400.degree. F.) by a factor of at least four in terms of strain reversals to failure in the range of 0.001 to 0.008 strain amplitude without deterioration of stress rupture life to temperatures as high as 1800.degree. F. when compared to the same cast nickel-base superalloy in the non-grain refined condition.
14. The improved composition of claim 13 wherein said grain refining agent is 0.1 percent boron.
15. The improved composition of claim 13 wherein said grain refining agent is a combination of 0.1 percent boron and 0.1 percent zirconium.
16. A new, improved cast nickel-base superalloy having a fine equiaxed grain structure and improved fatigue life at both room and elevated temperatures (1400.degree. F.), formed by a process involving: charging a nickel-base superalloy in a crucible; adding to said superalloy from 0.01 to 0.20 percent of a member selected from the group consisting of boron, zirconium and mixtures thereof for causing the formation of a substrate for heterogeneous nucleation; melting said charged nickel-base superalloy and said selected member in a vacuum furnace; superheating said charged nickel-base superalloy and said selected member to a temperature of about 250.degree. F. to about 400.degree. F. above said melting temperature in a period of about 2 minutes to about 8 minutes to form heterogeneous nuclei in said nickel-base superalloy; and cooling until partial solidification, reheating and pouring said superalloy with about 50.degree. to about 100.degree. F. of superheat, whereby an equiaxed fine grain structure results in said superalloy.
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| Patent | Date | Inventor | Cited By |
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| US3620719 | 1971-11-01 | Wheaton et al. |