US20100329883A1 - Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys - Google Patents

Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys Download PDF

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US20100329883A1
US20100329883A1 US12/494,896 US49489609A US2010329883A1 US 20100329883 A1 US20100329883 A1 US 20100329883A1 US 49489609 A US49489609 A US 49489609A US 2010329883 A1 US2010329883 A1 US 2010329883A1
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superalloy
worked article
grain size
article
gamma prime
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David Paul Mourer
Kenneth Rees Bain
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General Electric Co
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General Electric Co
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Priority to CA2707782A priority patent/CA2707782A1/en
Priority to JP2010144348A priority patent/JP2011012346A/ja
Priority to EP10167751A priority patent/EP2295612A1/en
Priority to CN2010102269828A priority patent/CN101935780A/zh
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/21—Manufacture essentially without removing material by casting

Definitions

  • the present invention generally relates to nickel-base superalloys and methods for processing such superalloys. More particularly, this invention relates to a nickel-base superalloy and a method of forging an article from the nickel-base superalloy to promote a more controlled grain growth during supersolvus heat treatment, such that the article is characterized by a microstructure with a finer uniform grain size and exhibits improved low cycle fatigue behavior.
  • the turbine section of a gas turbine engine is located downstream of a combustor section and contains a rotor shaft and one or more turbine stages, each having a turbine disk (rotor) mounted or otherwise carried by the shaft and turbine blades mounted to and radially extending from the periphery of the disk.
  • Components within the combustor and turbine sections are often formed of superalloy materials in order to achieve acceptable mechanical properties while at elevated temperatures resulting from the hot combustion gases. Higher compressor exit temperatures in modern high pressure ratio gas turbine engines can also necessitate the use of high performance nickel superalloys for compressor disks, blisks, and other components.
  • Suitable alloy compositions and microstructures for a given component are dependent on the particular temperatures, stresses, and other conditions to which the component is subjected.
  • airfoil components such as blades and vanes are often formed of equiaxed, directionally solidified (DS), or single crystal (SX) superalloys
  • turbine disks are typically formed of superalloys that must undergo carefully controlled forging, heat treatments, and surface treatments such as peening to produce a polycrystalline microstructure having a controlled grain structure and desirable mechanical properties.
  • Turbine disks are often formed of gamma prime ( ⁇ ′) precipitation-strengthened nickel-base superalloys (hereinafter, gamma prime nickel-base superalloys) containing chromium, tungsten, molybdenum, rhenium and/or cobalt as principal elements that combine with nickel to form the gamma ( ⁇ ) matrix, and contain aluminum, titanium, tantalum, niobium, and/or vanadium as principal elements that combine with nickel to form the desirable gamma prime precipitate strengthening phase, principally Ni 3 (Al,Ti).
  • gamma prime nickel-base superalloys include René 88DT (R88DT; U.S. Pat. No.
  • R88DT has a composition of, by weight, about 15.0-17.0% chromium, about 12.0-14.0% cobalt, about 3.5-4.5% molybdenum, about 3.5-4.5% tungsten, about 1.5-2.5% aluminum, about 3.2-4.2% titanium, about 0.5.0-1.0% niobium, about 0.010-0.060% carbon, about 0.010-0.060% zirconium, about 0.010-0.040% boron, about 0.0-0.3% hafnium, about 0.0-0.01 vanadium, and about 0.0-0.01 yttrium, the balance nickel and incidental impurities.
  • R104 has a nominal composition of, by weight, about 16.0-22.4% cobalt, about 6.6-14.3% chromium, about 2.6-4.8% aluminum, about 2.4-4.6% titanium, about 1.4-3.5% tantalum, about 0.9-3.0% niobium, about 1.9-4.0% tungsten, about 1.9-3.9% molybdenum, about 0.0-2.5% rhenium, about 0.02-0.10% carbon, about 0.02-0.10% boron, about 0.03-0.10% zirconium, the balance nickel and incidental impurities.
  • Another notable gamma prime nickel-base superalloy is disclosed in European Patent Application EP1195446, and has a composition of, by weight, about 14-23% cobalt, about 11-15% chromium, about 0.5-4% tantalum, about 0.5-3% tungsten, about 2.7-5% molybdenum, about 0.25-3% niobium, about 3-6% titanium, about 2-5% aluminum, up to about 2.5% rhenium, up to about 2% vanadium, up to about 2% iron, up to about 2% hafnium, up to about 0.1% magnesium, about 0.015-0.1% carbon, about 0.015-0.045% boron, about 0.015-0.15% zirconium, the balance nickel and incidental impurities.
  • Disks and other critical gas turbine engine components are often forged from billets produced by powder metallurgy (P/M), conventional cast and wrought processing, and spraycast or nucleated casting forming techniques.
  • Powder metallurgy P/M
  • Gamma prime nickel-base superalloys formed by powder metallurgy are particularly capable of providing a good balance of creep, tensile, and fatigue crack growth properties to meet the performance requirements of turbine disks and certain other gas turbine engine components.
  • a powder of the desired superalloy undergoes consolidation, such as by hot isostatic pressing (HIP) and/or extrusion consolidation.
  • HIP hot isostatic pressing
  • the resulting billet is then isothermally forged at temperatures slightly below the gamma prime solvus temperature of the alloy to approach superplastic forming conditions, which allows the filling of the die cavity through the accumulation of high geometric strains without the accumulation of significant metallurgical strains.
  • These processing steps are designed to retain the fine grain size originally within the billet (for example, ASTM 10 to 13 or finer), achieve high plasticity to fill near-net-shape forging dies, avoid fracture during forging, and maintain relatively low forging and die stresses.
  • Forged gas turbine engine components often contain grains with sizes of about ASTM 9 and coarser, such as ASTM 2 to 9, though a much tighter range is typically preferred, such as grain sizes within a limited range of 2 to 3 ASTM units. Such a limited range can be considered uniform, which as used herein refers to grain size and growth characterized by the substantial absence of non-uniform critical grain growth.
  • critical grain growth refers to localized excessive grain growth in an alloy that results in the formation of grains outside typical uniform grain size distributions whose size sufficiently exceeds the average grain size in the alloy (such as regions as coarse as ASTM 00 in a field of ASTM 6-10) to negatively affect the low cycle fatigue (LCF) properties of an article formed from the alloy, manifested by early preferential crack nucleation in the CGG regions.
  • Critical grain growth can also have a negative impact on other mechanical properties, such as tensile strength. Critical grain growth occurs during supersolvus heat treatment following hot forging operations in which a wide range of local strains and strain rates are introduced into the material.
  • critical grain growth is believed to be driven by excessive stored energy within the worked article, and may involve individual grains, multiple individual grains within a small region, or large areas of adjacent grains.
  • the grain diameters of the effected grains are often substantially coarser than the desired grain size.
  • Disks and other critical gas turbine engine components forged from billets produced by powder metallurgy and extrusion consolidation have appeared to exhibit a lesser propensity for critical grain growth than if forged from billets produced by conventional cast and wrought processing or spraycast forming techniques, but in any event are susceptible to critical grain growth during supersolvus heat treatment.
  • the maximum strain rate is composition, microstructure, and temperature dependent, and can be determined for a given superalloy by deforming test samples under various strain rate conditions, followed by a suitable supersolvus heat treatment.
  • the maximum (critical) strain rate is then defined as the strain rate that, if exceeded during deformation and working of a superalloy and accompanied by a sufficient amount of total strain, will result in critical grain growth after supersolvus heat treatment.
  • Another processing limitation identified by Krueger et al. as avoiding critical grain growth in a nickel-base superalloy having a gamma prime content of, for example, 30-46 volume percent and higher, is to ensure superplastic deformation of the billet during forging.
  • the billet is processed to have a fine grain microstructure that achieves a minimum strain rate sensitivity (m) of about 0.3 or greater for the superalloy within the forging temperature and strain rate ranges.
  • m strain rate sensitivity
  • the ability of a fine grain billet to deform superplastically is dependent on strain rate sensitivity, and superplastic materials exhibit a low flow stress as represented by the following equation:
  • ⁇ is the flow stress
  • K is a constant
  • ⁇ dot over ( ⁇ ) ⁇ is the strain rate
  • m is the strain rate sensitivity, with higher values of m corresponding to greater superplasticity.
  • Yoon et al. cites an upper limit strain rate of below about 0.032 per second (s ⁇ 1 ) for R88DT (identified by Raymond et al. as Alloy D).
  • Yoon et al. also identifies a maximum strain rate of not more than about 0.032 s ⁇ 1 , particularly in reference to forging R88DT (identified in Yoon et al. as Alloy A).
  • Yoon et al. further place an upper limit on the maximum strain rate gradient during forging, and requires extended annealing of the forging at a subsolvus temperature to remove stored strain energy prior to performing a supersolvus heat treatment.
  • the present invention provides a gamma prime precipitation-strengthened nickel-base superalloy and a method of forging an article from the superalloy to promote a more controlled grain growth during supersolvus heat treatment, such that the article is characterized by a microstructure with a finer uniform grain size and exhibits improved low cycle fatigue behavior.
  • the method includes formulating the superalloy to have a composition of, by weight, about 16.0-22.4% cobalt, about 6.6-14.3% chromium, about 2.6-4.8% aluminum, about 2.4-4.6% titanium, about 1.4-3.5% tantalum, about 0.9-3.0% niobium, about 1.9-4.0% tungsten, about 1.9-3.9% molybdenum, about 0.0-2.5% rhenium, greater than 0.05% and in certain embodiments greater than 0.1% carbon, at least 0.1% hafnium, about 0.02-0.10% boron, about 0.03-0.10% zirconium, the balance nickel and incidental impurities.
  • the superalloy is similar in composition to R104, with the notable exceptions that R104 does not contain hafnium and has a carbon content of 0.02-0.10 weight percent.
  • a billet is formed of the superalloy and worked at a temperature below the gamma prime solvus temperature of the superalloy so as to form a worked article. In particular, the billet is worked while maintaining strain rates as high as possible to control average grain size, but below an upper strain rate limit of greater than 0.03 per second to avoid critical grain growth.
  • the worked article is then heat treated at a temperature above the gamma prime solvus temperature of the superalloy for a duration sufficient to uniformly coarsen the grains of the worked article, after which the worked article is cooled at a rate sufficient to reprecipitate gamma prime within the worked article.
  • the cooled worked article has an average grain size of not coarser than ASTM 7 and preferably not coarser than ASTM 8, and is substantially free of grains in excess of three ASTM units coarser than the average grain size.
  • the superalloy has a sufficiently high carbon content and is forged at sufficiently high local strain rates so that, following a supersolvus heat treatment, the resulting forged component is characterized by a fine and substantially uniform grain size distribution. Also preferably avoided is critical grain growth that would produce individual grains or small regions of grains having grain sizes of more than five and preferably three ASTM units coarser than the average grain size in the component, or large regions that are uniform in grain size but with a grain size coarser than a desired grain size range of about two ASTM units. As a result, the forged component is capable of exhibiting improved mechanical properties, particularly low cycle fatigue behavior.
  • FIG. 1 is a schematic graph representing low cycle fatigue versus average grain size data for a variety of nickel-base superalloys.
  • FIG. 2 is a perspective view of a turbine disk of a type used in gas turbine engines.
  • FIG. 3 is a table listing a series of nickel-base superalloy compositions initially identified to evaluate the effects of carbon and hafnium contents on the low cycle fatigue behavior and hold time fatigue crack growth rate behavior.
  • FIG. 4 is a table listing a series of nickel-base superalloy compositions obtained and thermomechanically processed under various conditions, including those in accordance with embodiments of the present invention.
  • FIG. 5 is a table listing the compositions of FIG. 4 and average grain size resulting from the use of different forging conditions.
  • FIG. 6 shows four scanned images of two specimens from FIG. 4 .
  • FIG. 7 is a graph plotting average grain size versus carbon content, forging temperature, and forging rate for R104 and the specimens of FIG. 4 .
  • FIGS. 8 and 9 are graphs plotting the tensile strength behavior of three specimens of FIG. 5 versus ASTM grain size whose variation was achieved by the use of carbide enhanced grain size control.
  • the present invention is directed to gamma prime nickel-base superalloys, and particular those suitable for components produced by a hot working (e.g., forging) operation to have a polycrystalline microstructure.
  • a particular example represented in FIG. 2 is a high pressure turbine disk 10 for a gas turbine engine.
  • the invention will be discussed in reference to processing of a high-pressure turbine disk for a gas turbine engine, though those skilled in the art will appreciate that the teachings and benefits of this invention are also applicable to compressor disks and blisks of gas turbine engines, as well as numerous other components that are subjected to stresses at high temperatures and require low cycle fatigue and high temperature dwell capabilities.
  • Disks of the type shown in FIG. 2 are typically produced by isothermally forging a fine-grained billet formed by powder metallurgy (PM), a cast and wrought processing, or a spraycast or nucleated casting type technique. Such processes are carried out to yield a billet with a fine grain size, typically about ASTM 10 or finer, to achieve low flow stresses during forging.
  • the billet can be formed by consolidating a superalloy powder, such as by hot isostatic pressing (HIP) or extrusion consolidation.
  • HIP hot isostatic pressing
  • the billet is typically forged at a temperature at or near the recrystallization temperature of the alloy but less than the gamma prime solvus temperature of the alloy, and under conditions to enable filling of the forging die cavity through the accumulation of high geometric strains without the accumulation of significant metallurgical strains.
  • superplastic forming conditions corresponding to a strain rate sensitivity (m) of 0.3 or higher at the forging temperature
  • an aspect of the invention is that the billet can be worked without the forging process being fully superplastic, i.e., at strain rate sensitivity values of less than about 0.3, for example, non-superplastically at a strain rate sensitivity value of about 0.2 at the working (e.g., forging) temperature.
  • a supersolvus (solution) heat treatment is performed, during which grain growth occurs.
  • the supersolvus heat treatment is performed at a temperature above the gamma prime solvus temperature (but below the incipient melting temperature) of the superalloy to recrystallize the worked grain structure and dissolve (solution) the gamma prime precipitates in the superalloy.
  • the component is cooled at an appropriate rate to re-precipitate gamma prime within the gamma matrix or at grain boundaries, so as to achieve the particular mechanical properties desired.
  • the component may also be aged using known techniques with a short stress relief cycle at a temperature above the aging temperature of the alloy if desirable to reduce residual stresses.
  • a supersolvus heat treatment of a type described above has typically yielded an acceptable but not wholly optimal average grain size range of about ASTM 5 to 7, with the result that the low cycle fatigue behavior of the resulting turbine disk is less than optimal, particularly at temperatures of about 400° F. to about 800° F. (about 200° C. to about 425° C.).
  • the present invention provides modifications to the chemistry of R104 to control and limit grain growth during supersolvus heat treatment to achieve and maintain a finer grain size following supersolvus heat treatment, as well as avoid critical grain growth.
  • a finer and more controllable average grain size can be achieved by modifying the R104 alloy to have a relatively high carbon content, for example, greater than 0.05 weight percent carbon and in some cases greater than 0.1 weight percent carbon.
  • improved high temperature dwell behavior can be achieved by modifying the R104 alloy to contain at least 0.1 weight percent hafnium.
  • grain refinement can be further promoted by utilizing relatively high strain rates and relatively low temperatures during forging.
  • a series of targeted alloy compositions were defined (by weight percent) as set forth in a table in FIG. 3 .
  • the targeted compositions reflect the intent to evaluate alloys with carbon contents at and above the maximum carbon content of 0.1 weight percent for R104, as well as additions of hafnium.
  • nine alloys were procured whose actual chemistries are indicated in a table in FIG. 4 .
  • Processing of the alloys included consolidating a powder of the alloy compositions to produce multiple billets of each alloy, which were then hot worked (forged) followed by a supersolvus heat treatment. Two sets of forging conditions were used.
  • a first, referred to as “Hot/Slow” in FIG. 5 entailed forging conditions that included a maximum strain rate of about 0.003/sec at a forging temperature of about 2060° F. (about 1130° C.).
  • the second, referred to as “Conventional” in FIG. 5 entailed forging conditions that included a conventional maximum strain rate of about 0.03/sec at a forging temperature of about 1925° F. (about 1050° C.).
  • the supersolvus heat treatments were performed at a temperature of about 2140° F. (about 1170° C.), which is above the gamma prime solvus temperature (but below the incipient melting temperature) of R104. During the heat treatment, the worked grain structures of the forged specimens were recrystallized and the gamma prime precipitates were dissolved (solutioned).
  • the specimens were cooled at rates that ensured re-precipitation of gamma prime within the gamma matrix or at grain boundaries.
  • a controlled air cooling was employed to yield an approximately constant cooling rate of about 200° F./minute for all specimens.
  • the specimens were aged at about 1550° F. (about 845° C.) for about four hours, followed by about eight hours at about 1400° F. (about 760° C.).
  • FIG. 5 indicates the average ASTM grain size observed for each alloy composition. From FIG. 5 , it can be seen that the “Hot/Slow” forging method produced significantly coarser grains than the “Conventional” forging method. The finer average grain sizes observed in the latter, which were typically ASTM 8 or finer, would be expected to promote improved mechanical properties of the forged specimens, including low cycle fatigue resistance, tensile strength, fatigue strength, and other mechanical properties desired for a turbine or compressor disk.
  • the critical strain rate is then defined as the strain rate that, if exceeded during deformation and working of a superalloy and accompanied by a sufficient amount of total strain, will result in critical grain growth after supersolvus heat treatment.
  • the upper strain rate limit for the alloy specimens is greater than 0.03 per second, and possibly as high as 0.32 per second.
  • FIG. 6 contains scanned images of two microphotographs of the forged specimen identified as 101 B in FIG. 5 , as well as scanned images of two microphotographs of a forged R104 specimen.
  • the images evidence that the carbide network within the 101 B specimen was significantly increased over that of R104.
  • the increased carbide network was attributed to the high carbon content and the presence of hafnium in the 101 B specimen.
  • hafnium is a strong primary MC carbide former the hafnium content of the 101 B specimen may have promoted the formation of highly stable carbides, contributing to high temperature carbide stability and aiding in the ability to control grain size by the dispersion of primary MC carbides in the matrix.
  • FIG. 7 is a plot comparing ASTM average grain size versus carbon content, and evidences the significant influence carbon content had on average grain size in the forged specimens. For example, at forging temperatures of about 2060° F. (about 1130° C.) carbon contents above 0.1 weight percent resulted in average grain sizes of finer than ASTM 7, and at forging temperatures of about 1925° F. (about 1050° C.) carbon contents above 0.05 weight percent and above 0.1 weight percent resulted in average grain sizes of finer than ASTM 8 and ASTM 8.5, respectively. On the basis of FIG. 1 , the finer average grain sizes achieved with the higher carbon contents would be expected to correspond to improved low cycle fatigue resistance.
  • FIG. 1 the finer average grain sizes achieved with the higher carbon contents would be expected to correspond to improved low cycle fatigue resistance.
  • FIGS. 8 and 9 show tensile behavior and ductility at about 800° F. (about 425° C.) versus ASTM grain size. Improved tensile properties were attributed to the presence of increased carbon and the forging technique used, resulting in refining of the specimen grain size.
  • compositions and weight percent ranges were devised for the purpose of obtaining improvements in low cycle fatigue resistance and dwell crack growth behavior over the conventional R104 superalloy. These compositions and ranges are set forth below in Table I.

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US12/494,896 US20100329883A1 (en) 2009-06-30 2009-06-30 Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys
CA2707782A CA2707782A1 (en) 2009-06-30 2010-06-17 Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys
JP2010144348A JP2011012346A (ja) 2009-06-30 2010-06-25 スーパーソルバス熱処理ニッケル基超合金の最終結晶粒径を制御し改善する方法
EP10167751A EP2295612A1 (en) 2009-06-30 2010-06-29 Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys
CN2010102269828A CN101935780A (zh) 2009-06-30 2010-06-30 控制和细化经超溶线热处理镍基超合金中最终粒度的方法

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EP2520679A1 (en) * 2011-05-05 2012-11-07 General Electric Company Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby
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CN103866162A (zh) * 2014-03-02 2014-06-18 王文姣 一种具有高裂纹扩展抗力的镍基粉末冶金高温合金
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