Patent application number | Description | Published |
20090000706 | METHOD OF CONTROLLING AND REFINING FINAL GRAIN SIZE IN SUPERSOLVUS HEAT TREATED NICKEL-BASE SUPERALLOYS - A method of forming a component from a gamma prime precipitation-strengthened nickel-base superalloy. The method entails formulating the superalloy to have a sufficiently high carbon content and forging the superalloy at sufficiently high local strain rates so that, following a supersolvus heat treatment, the component is characterized by a fine and substantially uniform grain size distribution, preferably finer than ASTM 7 and more preferably in a range of about ASTM 8 to 10. | 01-01-2009 |
20100303665 | NICKEL-BASE SUPERALLOYS AND COMPONENTS FORMED THEREOF - A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight, 16.0 to 30.0% cobalt, 11.5 to 15.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 1.5 to 6.0% titanium, up to 5.0% tungsten, 1.0 to 7.0% molybdenum, up to 3.5% niobium, up to 1.0% hafnium, 0.02 to 0.20% carbon, 0.01 to 0.05% boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.5 to 2.0. | 12-02-2010 |
20100303666 | NICKEL-BASE SUPERALLOYS AND COMPONENTS FORMED THEREOF - A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight, 18.0 to 30.0% cobalt, 11.4 to 16.0% chromium, up to 6.0% tantalum, 2.5 to 3.5% aluminum, 2.5 to 4.0% titanium, 5.5 to 7.5% molybdenum, up to 2.0% niobium, up to 2.0% hafnium, 0.04 to 0.20% carbon, 0.01 to 0.05% boron, 0.03 to 0.09% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.71 to 1.60. | 12-02-2010 |
20100329876 | NICKEL-BASE SUPERALLOYS AND COMPONENTS FORMED THEREOF - Gamma prime nickel-base superalloy and components formed therefrom. The alloy contains, by weight, 11.3 to 13.3% cobalt, 12.4 to 15.2% chromium, 2.1 to 2.7% aluminum, 3.6 to 5.8% titanium, 3.5 to 4.5% tungsten, 3.1 to 3.8% molybdenum, 0.0 to 1.2% niobium, 0.0 to 2.3% tantalum, 0.0 to 0.5% hafnium, 0.040 to 0.100% carbon, 0.010 to 0.046% boron, 0.030 to 0.080% zirconium, the balance nickel and impurities, wherein the Nb+Ta content is 0.0-3.5%. | 12-30-2010 |
20100329883 | METHOD OF CONTROLLING AND REFINING FINAL GRAIN SIZE IN SUPERSOLVUS HEAT TREATED NICKEL-BASE SUPERALLOYS - A gamma prime precipitation-strengthened nickel-base superalloy and method of forging an article from the superalloy to promote a low cycle fatigue resistance and high temperature dwell behavior of the article. The superalloy has a composition of, by weight, 16.0-22.4% cobalt, 6.6-14.3% chromium, 2.6-4.8% aluminum, 2.4-4.6% titanium, 1.4-3.5% tantalum, 0.9-3.0% niobium, 1.9-4.0% tungsten, 1.9-3.9% molybdenum, 0.0-2.5% rhenium, greater than 0.05% carbon, at least 0.1% hafnium, 0.02-0.10% boron, 0.03-0.10% zirconium, the balance nickel and incidental impurities. 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, which is then heat treated above the gamma prime solvus temperature of the superalloy to uniformly coarsen the grains of the article, after which the article is cooled to reprecipitate gamma prime. The article has an average grain size of not coarser than ASTM 7 and is substantially free of critical grain growth. | 12-30-2010 |
20110194940 | WELDING PROCESS AND COMPONENT PRODUCED THEREFROM - A process of fabricating a rotating component and components formed thereby. The process includes fabricating preforms corresponding to portions of the component. Each preform has an interface surface at which the preforms can be joined to locate a first of the portions in a radially outward direction from a second of the portions. The preforms are then inertia welded together to form a profile having a solid-state weld joint containing a finer-grained material than other portions of the profile. The profile is then forged with dies to produce a forging. At least one of the dies has a recess into which the finer-grained material from the weld joint is expelled during forging to purge a joint region of the forging between the forging portions of the finer-grained material. The joint region contains grains distorted in an axial direction of the forging. | 08-11-2011 |
20110203707 | NICKEL-BASE ALLOY, PROCESSING THEREFOR, AND COMPONENTS FORMED THEREOF - A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and dwell fatigue crack growth behavior. The superalloy contains, by weight, 10.00 to 22.0% cobalt, 10.0 to 14.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 2.0 to 6.0% titanium, 1.5 to 5.0% tungsten, 1.5 to 5.0% molybdenum, 1.0 to 3.5% niobium, 0.05 to 0.6% hafnium, 0.02 to 0.10% carbon, 0.01 to 0.40% boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.7 to 1.5. The superalloy is hot worked and heat treated to contain cellular gamma prime precipitates that distort grain boundaries, creating tortuous grain boundary fracture paths that are believed to promote the fatigue crack growth resistance of the superalloy. | 08-25-2011 |
20110206523 | WELDING PROCESS AND COMPONENT FORMED THEREBY - A process of fabricating a rotating component and a rotating component formed thereby. The rotating component has a rotational axis, at least one rim member, at least one disk member, and at least one airfoil member. The rim and disk members are welded together to define a first solid-state weld joint lying in a first plane that is not parallel to the rotational axis of the rotating component. The airfoil member is welded to the rim member to define a second solid-state weld joint lying in a second plane that is not parallel to the rotational axis of the rotating component. The rim member is located in a radially outward direction from the disk member, and the airfoil member is located in a radially outward direction from the rim member. | 08-25-2011 |
20120279067 | COMPONENTS AND PROCESSES OF PRODUCING COMPONENTS WITH REGIONS HAVING DIFFERENT GRAIN STRUCTURES - Processes for fabricating components to have two or more regions with different grain structures, and components produced by such processes. First and second preforms are fabricated to comprise interface surfaces at which the preforms can be joined together. The first and second preforms are formed of first and second precipitation-strengthened alloys, respectively, and the first alloy differs from the second alloy by having a higher solvus temperature or a higher grain refiner content. The preforms are joined together to form an article comprising first and second portions formed by the first and second preforms, respectively, and corresponding to first and second regions of the component, respectively, and the interface surfaces of the preforms form a joint between the first and second portions of the article. A supersolvus heat treatment is performed on the article so that greater grain growth occurs in the second portion than in the first portion. | 11-08-2012 |
20120305143 | COMPONENTS AND PROCESSES OF PRODUCING COMPONENTS WITH REGIONS HAVING DIFFERENT GRAIN STRUCTURES - Processes for fabricating components to have two or more regions with different grain structures, and components produced by such processes. The processes entail performing at least one forging step on a preform to produce a profile having at least a first portion corresponding to the first region of the component. The preform is formed of a precipitation-strengthened alloy having a solvus temperature, and the at least one forging step comprises a nonfinal forging step performed at a first strain rate and at a first subsolvus temperature that is below the solvus temperature of the alloy. A subsequent forging step is performed on the profile to produce a final profile comprising the first portion and a second portion corresponding to the second region of the component. The subsequent forging step is performed at a strain rate and at a subsequent subsolvus temperature, wherein at least one of the subsequent strain rate and subsequent subsolvus temperature is either higher or lower than the first strain rate or first subsolvus temperature. A heat treatment is then performed on the final profile to cause grain growth, wherein the first portion of the final profile has a different grain size than the second portion. | 12-06-2012 |
20130167979 | METHOD OF PREDICTING QUENCH CRACKING IN COMPONENTS FORMED BY HIGH DEFORMATION PROCESSES - A process for heat treating a component formed of an alloy. The process includes manipulating uniaxial strain test data of the alloy using a triaxiality factor to determine an equivalent multiaxial stress state. Conditions are then applied to the multiaxial stress state to identify a cooling path for the component. The cooling path includes boundaries for heat treatment temperatures and cooling rates that do not exceed predetermined stresses or strains and/or avoid predetermined residual stress patterns in the alloy. The component is then heated to a heat treatment temperature and quenched according to the cooling path identified in the applying step. | 07-04-2013 |
20140205449 | SUPERALLOYS AND COMPONENTS FORMED THEREOF - A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities. The superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours. | 07-24-2014 |