OXIDE DISPERSION-STRENGTHENED ALLOY HAVING HIGH STRENGTH AT INTERMEDIATE TEMPERATURES

Abstract: Oxide dispersion-strengthened alloys containing 5 to 9% chromium, 5 to 7% aluminium, 5 to 9% tungsten, 1 to 3% molybdenum, 1 to 5% tantalum, 0 to 1.5% titanium, 0 to 10% cobalt, 1 to 4% rhenium, 0.1 to 2% yttrium oxide, small amounts of boron and zirconium as required, balance essentially nickel, display excellent lives to rupture under load at intermediate high temperatures of about 850°C.

Description: The present invention is concerned with high temperature resistant nickel-base alloys and, more particularly, with such alloys containing strengthening oxide dispersions and made by mechanical alloying. The applicant has previously disclosed, e.g. in US-A-4 386 976, certain alloy compositions made by mechanical alloying which contain strengthening dispersions of oxide containing yttrium and which have, as a chief virtue, useful strength and other mechanical characteristics at very high temperatures about 1093°C (2000°F). At such very high temperatures, traditional nickel-base alloys which obtain their strength by a combination of solid solution matrix strengthening and precipitation hardening based upon the formation of gamma prime (Ni₃Al) precipitate tend to lose their strength. Essentially, the gamma prime precipitate dissolves in the solid matrix metal leaving the alloy with the strength of only the matrix solid solution. Oxide dispersion-strengthened (ODS) alloys such as those known as INCONEL™ alloy MA754, INCONEL™ alloy MA6000 and Alloy 51 retain useful amounts of strength at about 1093°C but tend to be less strong than some traditional nickel-base alloys, particularly in cast single crystal form, at intermediate high temperatures of about 850°C (1562°F). Nominal compositions in percent by weight, omitting small effective amounts of boron and/or zirconium, of some known ODS alloys are set forth in Table I. Alloy 51 is disclosed in US-A-4 386 976. Element Alloy INCONEL Alloy MA754 INCONEL Alloy MA6000 Alloy 51 Ni Bal. Bal. Bal. Cr 20 15 9.3 Al 0.3 4.5 8.5 Ti 0.5 2.5 - C 0.05 0.05 0.05 W - 4.0 6.6 Mo - 2.0 3.4 Ta - 2.0 - Y₂O₃ 0.6 1.1 1.1 The problem solved by the present invention is the provision of ODS alloys which retain useful strength at very high temperatures and which approach or exceed the strengths of traditional nickel-base alloys at intermediate high temperatures of about 850°C. This combination of strength characteristics is important in an ODS alloy because the ultimate use of this type of alloy is often in blades and other components in the hot sections of gas turbine engines. Such components do not experience one temperature but rather, usually, a wide range of temperatures while subjected to various stress levels depending generally in part on the configuration of the component. For example, the root portion of a turbine blade will be relatively cool but under a high rotationally induced stress. The leading and trailing edges of the selfsame blade will generally experience the hottest temperatures existing at a given height level on the blade, with rotationally induced stresses decreasing with height. All in all, an alloy suitable for a gas turbine blade cannot seriously sacrifice strength, ductility, etc., at one temperature for improvement at another temperature without putting severe restraints on the designer of the blade. The present invention provides a new and useful ODS nickel-base alloy which contains, in percent by weight, 5 to 9% chromium, 5 to 7% aluminium, 5 to 9% tungsten, 1 to 3% molybdenum, 1 to 5% tantalum, 0 to 1.5% titanium, 0 to 10% cobalt, 1 to 4% rhenium, 0.1 to 2% of an oxidic form of yttrium, with the proviso that this content is at least 0.6% when the alloy is in polycrystalline form and not more than 1% when the alloy is in single crystal form, 0.005 to 0.1% boron, 0.03 to 0.5% zirconium, up to 2% iron, up to 0.3% nitrogen, up to 1% niobium and up to 2% hafnium, with the balance being essentially nickel. Advantageously, the alloys of the invention contain about 0.03 to 0.3% zirconium and about 0.005 to 0.03% boron and are substantially free from niobium and/or hafnium. When the alloy of the invention is in the single crystal form, the amounts, if any, of grain boundary segregating elements such as boron, zirconium, carbon and hafnium should be as low as possible, i.e. they should be substantially or wholly absent. The alloy is advantageously in the form of a polycrystalline, directionally recrystallised metallic mass in which the aspect ratio (ratio of length to width) of the grains has an average value of at least 7 and which, subsequent to directional recrystallisation, has been heat treated for about 0.5 to 3 hours at 1275-1300°C, air cooled, then held for 1 to 4 hours at 940-970°C, air cooled and held for 12 to 48 hours at 820-860°C, after which the directionally recrystallised mass is finally air cooled. A most advantageous aspect of the present invention is an alloy composition in which the content of aluminium plus titanium is about 7.5 and the rhenium content is about 3%. When these latter criteria are observed, the ODS alloy of the present invention compared to prior nickel-base ODS alloys suffers substantially no disincrement of strength at temperatures over 1000°C while providing enhanced strength at intermediate temperatures of about 850°C. ODS alloy compositions of the present invention in terms of make-up charge to an attritor or ball mill are set forth in weight percent in Table II. Element Alloy A B C Cr 8 8 9 Al 6.5 6.5 7 W 6 6 6 Mo 1.5 1.5 2 Re 3 3 3 Ta 3 3 1 Ti - 1 - Co 5 5 - B 0.01 0.01 0.01 Zr 0.15 0.15 0.15 Y₂O₃ 1.1 1.1 1.1 Generally speaking, the alloys of the present invention may be produced by mechanically alloying powdered elemental and/or master-alloy constituents along with oxidic yttrium in an attritor or a horizontal ball mill in the presence of hardened steel balls until substantially saturation hardness is obtained along with thorough interworking of the attrited metals one within another and effective inclusion of an oxide containing yttrium within attrited alloy particles to provide homogeneity. Good results are achieved when the milling charge includes powder of an omnibus master alloy, i.e. an alloy containing all non-oxidic alloying ingredients in proper proportion except for being poor in nickel or nickel and cobalt. This omnibus master alloy powder can be produced by melting and atomization, e.g. gas atomization or melt spinning. The mill charge consists of the master alloy plus oxidic yttrium and appropriate amounts of nickel or nickel and cobalt or nickel-cobalt alloy powder. The iron content of the milled alloys of the invention is advantageously limited to 1% maximum, an amount which under usual circumstances may be picked up during mechanical alloying processing. The attrited powder is then screened, blended and packed into mild steel extrusion cans which are sealed and degassed, if required. The sealed cans are then heated to about 1000-1200°C and hot-extruded at an extrusion ratio of at least about 5 using a relatively high strain rate. After extrusion or equivalent hot compaction, the thus processed mechanically alloyed material can be hot-worked, especially directionally hot-worked by rolling or the like. This hot-working should be carried out rapidly in order to preserve in the metal a significant fraction of the strain energy induced by the initial extrusion or other hot compaction. Once this is done, the alloys of the invention are processed by any suitable means applicable to the solid stage, e.g. zone annealing, to provide a coarse elongated grain structure in the body of said grains (or grain in the case of a single crystal) having an average grain aspect ratio (GAR) of at least 7. Zone annealing of the alloys of the present invention can advantageously be carried out at temperatures of about 1265-1308°C and at differential speeds between a sharply fronted annealing zone and a body of the alloy of the invention of about 50 to 100 mm/hr. For examples reported in the present specification the differential speed of zone annealing was kept constant at about 76 mm/hr. The directional recrystallisation temperature was varied and shown to exert an appreciable influence on the bar properties. The approximate recrystallisation temperature may be estimated from gradient annealing studies of the unrecrystallised bar. Experience indicates that the secondary recrystallisation temperature is associated with the gamma prime solvus temperature in these gamma/gamma prime phase superalloys. Generally, the recrystallisation temperature is observed to be higher than the gamma prime solvus temperature with the latter perhaps being the lower limit and the incipient melting point being the upper temperature limit. The directional recrystallisation response and therefore the ultimate structure/properties of the alloy may, therefore, be influenced by the directional recrystallisation temperature. For example, better high temperature stress rupture properties in alloy B were obtained when the alloy was directionally recrystallised at about 1290°C (see B1 results in Tables III/III-A) than at about 1265°C (see B2 results in Tables III/III-A). The differences in mechanical characteristics are attributed, inter alia, to a more favourable grain aspect ratio and more uniform grain structure obtained when this alloy was directionally recrystallised at 1290°C. After zone annealing, machining and any other shaping process to achieve final or semi-final product configuration, the alloy of the present invention is heat treated in the solid state by solution annealing at 1275-1300°C, e.g. by maintaining 20 mm diameter rod at 1288°C for one hour followed by air cooling. The alloys are then hardened by heating in the range of about 925-1000°C for about 1 to 12 hours, air cooling and then holding at a temperature of about 830-860°C for 12 to 60 hours followed by air cooling. A particularly advantageous heat treatment used in each example reported in this specification comprises solution annealing for 1 hour at 1288°C following by heating for 2 hours at 954°C, air cooling and maintaining the alloy at 843° for 24 hours prior to final cooling to room temperature. Stress rupture testing results for alloys A, B and C at various temperatures and stresses are set forth in Tables III and III-A. Alloy Test Condition 850°C-379 MPa 1093°C-138 MPa Life (h) El (%) RA (%) Life (h) El (%) RA (%) A 508.7 1.2 2.4 8.8 0.1 3.2 B1 1202.4 3.1 5.1 1107.5 0.5 0.1 B2 955.9 0.5 3.2 40.0 1.5 0.8 C 771.8 3.0 6.3 904.3 2.4 0.1 51 232.5 91.6 MA6000 100 - Alloy Test Condition 760°C-655 MPa 850°C-500 MPa 1093°C-165.5 MPa Life (h) El (%) RA (%) Life (h) El (%) RA (%) Life (h) El (%) RA (%) A 55.8 2.9 4.0 45.3 1.2 4.3 3.8 1.3 3.9 B1 239.0 1.2 5.5 124.4 2.5 6.3 30.9 1.4 3.1 B2 297.1 1.1 3.1 64.1 0.7 0.8 6.7 2.0 0.8 C 403.0 1.8 3.2 109.4 2.0 4.3 25 1.9 3.9 51 127.6 (at 586 MPa) The data in Tables III and III-A shows that the alloys of the present invention have usable lives to rupture under load at 760°C and 1093°C and lives to rupture at 850° significantly better than such lives to rupture at 850°C of prior known ODS alloys. For example, given the same heat treatment, Alloy 51 and INCONEL alloy MA6000 lasted 232.5 and 100 hours respectively at 850°C under a load of 379 MPa. Table III shows that the alloys of the present invention lasted at least twice as long as Alloy 51 under these test conditions. The best of the alloys of the present invention, i.e. alloys B1 and C, show lives to rupture under all conditions tested significantly superior to those of Alloy 51 and INCONEL alloy MA6000. At the intermediate high temperature of 850°C these alloys are capable of lasting 3 to 6 times longer under stress than Alloy 51 and 7 to 12 times longer than INCONEL alloy MA6000. While specific embodiments of the invention are illustrated and described herein, those skilled in the art will understand that the invention is not limited to these embodiments.

Claims: An oxide dispersion strengthened alloy consisting in percent by weight of 5 to 9% chromium, 5 to 7% aluminium, 5 to 9% tungsten, 1 to 3% molybdenum, 1 to 5% tantalum, 0 to 1.5% titanium, 0 to 10% cobalt, 1 to 4% rhenium, 0.1 to 2% of an oxidic form of yttrium, 0.005 to 0.1% boron, 0.03 to 0.5% zirconium, 0 to 2% iron, 0 to 0.3% nitrogen, 0 to 1% niobium and 0 to 2% hafnium with the balance, apart from impurities, being nickel, with the provisos that said alloy, when in polycrystalline form, contains at least about 0.6% of an oxidic form of yttrium and that, when in single crystal form, it contains not more than 1% of an oxidic form of yttrium and is substantially or wholly free from grain boundary segregating elements. An alloy as claimed in claim 1 in the form of a polycrystalline mass having elongated grain structure, in which the grains have an average aspect ratio of at least 7. An alloy as claimed in claim 1 in the form of a monocrystalline mass having a crystal aspect ratio of at least 7. An alloy as claimed in claim 1 containing about 3% rhenium. An alloy as claimed in claim 2 having a total Ti+Al content of at least 7% and at least 3% rhenium. An alloy as claimed in claim 5 having a total Ti+Al content of about 7.5% and a rhenium content of about 3%. An alloy according to any one of claims 1, 2, 4, 5 and 6 in the form of a polycrystalline, directionally recrystallised metallic mass in which the aspect ratio of the grains averages at least 7 and which, subsequent to directional recrystallisation, has been heat treated for 0.5 to 3 hours at 1275-1300°C, air cooled, held for 1 to 4 hours at 940-970°C, and cooled, held for 12 to 48 hours at 820-860°C and finally air cooled. A process of producing an alloy according to any preceding claim which includes the steps of directional recrystallisation by zone annealing in the temperature range between the gamma prime solvus temperature and the incipient melting point, shaping to final or semi-final shape, solution annealing and ageing. A process according to claim 8 wherein the solution annealing is performed at 1275-1300°C and the ageing comprises heating in the range of 925-1000°C, air cooling and then holding at a temperature of 830-860°C.

Inventors: BENN, RAYMOND CHRISTOPHER, ZOZOM, ANDREW
Applicants: INCO ALLOYS INTERNATIONAL, INC.
Application year: 1989
Main classification: C22C32
IPC codes: C22C32, C22C19