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

A technology of nickel-based superalloys and superalloys, which can be used in engine manufacturing, blade support elements, machines/engines, etc., and can solve problems such as not being able to obtain optimal mechanical properties.

Inactive Publication Date: 2011-01-05
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While existing forging methods of the type described above have achieved grain sizes in the ASTM 5 to 8 range, they still do not achieve optimum mechanical properties

Method used

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

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Embodiment Construction

[0024] The present invention relates to gamma prime nickel-based superalloys, particularly those suitable for use in components produced by hot working (eg, forging) operations so as to have a polycrystalline microstructure. figure 2 The particular example shown in is a high pressure turbine disk 10 of a gas turbine engine. The present invention will be discussed in connection with the machining of high pressure turbine disks for gas turbine engines, but those skilled in the art will appreciate that the teachings and benefits of the present invention are also applicable to compressor disks and blisks for gas turbine engines and numerous other Components subjected to stress and requiring low cycle fatigue and high temperature dwell capability.

[0025] figure 2 Discs of the type shown in are typically produced by isothermal forging of fine-grained billets formed by powder metallurgy (PM), casting and forging processes, or techniques of the spray casting or nucleation casting...

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Abstract

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.

Description

technical field [0001] Generally, the present invention relates to nickel-based superalloys and methods of processing such superalloys. More particularly, the present invention relates to a nickel-based superalloy and articles forged from said nickel-based superalloy to promote more controlled grain growth during supersolvus heat treatment so that said articles are characterized by having finer A method for uniform grain size microstructures exhibiting improved low cycle fatigue properties. Background technique [0002] The turbine section of a gas turbine engine is located downstream of the combustor section and contains a rotor shaft and one or more turbine stages, each turbine stage having a turbine disk (rotor) mounted on or otherwise carried by the shaft and Turbine blades mounted to and extending radially from the periphery of the disk. Components within the combustor and turbine sections are often formed from superalloy materials to obtain acceptable mechanical prop...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22F1/10F01D5/02
CPCC22C19/057C22C19/03C22F1/10C22C19/056F05B2230/21
Inventor D·P·穆雷尔K·R·贝恩
Owner GENERAL ELECTRIC CO
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