General Electric Company

Other

Samuel Vinod Thamboo

Michael F Henry

Raymond Joseph Stonitsch

Matthew Joseph Alinger

Richard DiDomizio

Ling Yang

Sarwan Kumar Mannan

Mark Gilbert Benz

William Thomas Carter

Bruce Alan Knudsen

Don Mark Lipkin

Robert John Zabala

Canan Uslu Hardwicke

Michael Francis Xavier Gigliotti

Liang Jiang

Elena Rozier

John J deBarbadillo, Ii

Richard Didomizio

Elena Rozier Gearing

John Joseph deBarbadillo, Ii

A formed article comprising a nanostructured ferritic alloy is provided. Advantageously, the article is not formed via extrusion, and thus, cost savings are provided. Methods are also provided for forming the article, and the articles so produced, exhibit sufficient continuous cycle fatigue crack growth resistance and hold time fatigue crack growth resistance to be utilized as turbomachinery components, and in particular, large, hot section components of a gas or steam turbine engines. In other embodiments, a turbomachinery component comprising an NFA is provided, and in some such embodiments, the turbomachinery component may be extruded.

Methods for processing nanostructured ferritic alloys, and articles produced thereby

An article includes a first section extending from an outer periphery to a predetermined surface located inward from the outer periphery. The first section comprises a nanostructured ferritic alloy. The article includes a second section extending from an inner periphery to the predetermined surface located outward from the inner periphery. The second section comprises at least one other alloy different from the nanostructured ferritic alloy.

Multi-alloy article, and method of manufacturing thereof

A method for heat treating a serviced turbine part to improve a hold time fatigue cracking resistance of the serviced turbine part is provided. The method includes positioning the serviced turbine part in a vacuum furnace configured to limit surface oxidation. The serviced turbine part is controllably heated to prevent distortion. A surface damage layer is recrystallized into a fine grain structure to prevent fatigue crack initiation. The serviced turbine part is controllably cooled to prevent distortion.

Method for heat treating serviced turbine part

Disclosed herein is a turbine component comprising a substrate; and a protective structure formed on the substrate, wherein the protective structure comprises an &#x3b1;-&#x3b2; titanium alloy, a &#x3b2;-titanium alloy or a near-&#x3b2; titanium alloy. Disclosed herein too is a process for providing a protective structure to a turbine component, comprising affixing a protective structure on a turbine component; wherein the protective structure comprises an &#x3b1;-&#x3b2; titanium alloy, a near-&#x3b2; titanium alloy or a &#x3b2;-titanium alloy.

Erosion and wear resistant protective structures for turbine components

An article, such as a turbine engine component, formed from a nickel-base superalloy, the nickel-base superalloy containing a &#x3b3;&#x2033; tetragonal phase and comprising aluminum, titanium, tantalum, niobium, chromium, molybdenum, and the balance nickel, wherein the article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100&#xb0; F. in the presence of steam. The invention also includes a nickel-base superalloy for forming such and article and methods of forming the article and making the nickel-base superalloy.

Nickel-base superalloys and articles formed therefrom

A method of heat treating a turbine rotor disk to obtain different radial properties at different locations in the rotor disk includes a) heating the rotor disk for a period of from 4 to 10 hours at a temperature of 1800&#xb0; F.; b) cooling the rotor disk to a temperature of about 1550&#xb0; F.; c) holding the rotor disk at about 1550&#xb0; F. for a period of from about 2 to about 4 hours; d) cooling the rotor disk to room temperature; e) precipitation aging the rotor disk by heating the rotor disk to temperature of 1325&#xb0; F. for 8 hours, holding it at 1150&#xb0; F. for 8 hours, and f) cooling the rotor disk.

Turbine rotor heat treatment process

An article, such as a turbine engine component, formed from a nickel-base superalloy, the nickel-base superalloy containing a &ggr;&Prime; tetragonal phase and comprising aluminum, titanium, tantalum, niobium, chromium, molybdenum, and the balance nickel, wherein the article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100&deg; F. in the presence of steam. The invention also includes a nickel-base superalloy for forming such and article and methods of forming the article and making the nickel-base superalloy.

Large forging manufacturing process

An article that comprises a fine-grain, homogeneous microstructure is essentially oxide- and sulfide-free and segregation defect free. The article is produced by a process that comprises forming a source of clean refined metal that has oxides and sulfides refined out by electroslag refining; and forming the article by nucleated casting. The invention also sets forth the article made by a system for implementing the clean metal nucleated casting process.

Clean melt nucleated cast article

In a method of forging an IN 706 alloy component, the component is forged at about 1750.degree. F. to 1825.degree. F. The component is cooled by quenching to minimize the formation of embrittling grain boundary phases, and subsequently air cooled to prevent surface cracking in the forging. The component is aged to precipitate gamma prime. Preferably, the quenching is performed to lower the temperature throughout the component below about 1500.degree. F.

Growing community of inventors

Latham, NY, United States of America

Samuel Vinod Thamboo