General Electric Company

Ge Medical Systems Global Technology Company, LLC

University of Virginia

General Electric Technology Gmbh

Pazhayannur Ramanathan Subramanian

Bernard Patrick Bewlay

Richard DiDomizio

Judson Sloan Marte

Timothy Joseph Trapp

Michael Francis Xavier Gigliotti, Jr

Luana Emiliana Iorio

Earl Claude Helder

Melvin Robert Jackson

Dennis Michael Gray

Shenyan Huang

Akane Suzuki

Joseph David Rigney

Michael Francis Xavier Gigliotti

Paul Leonard Dupree

Min Zou

Kathleen Blanche Morey

Voramon Supatarawanich Dheeradhada

Wanming Zhang

Steve John Buresh

Andrew John Elliott

Ramgopal Darolia

Jon Conrad Schaeffer

Kripa K Varanasi

Ji-Cheng Zhao

Carey Shawn Rogers

Yuk-Chiu Lau

David Edwin Budinger

Krishnamurthy Anand

Francis Johnson

Laurent Cretegny

Tao Deng

Steven Alfred Tysoe

Timothy Hanlon

Margaret Louise Blohm

Raghavendra Rao Adharapurapu

Jeffrey Jon Schoonover

Nitin Bhate

Richard Arthur Nardi, Jr

Srinidhi Sampath

Srihari Balasubramanian

Ming Feng Hsu

Ramkumar Kashyap Oruganti

Deborah D Whitis

William Dwight Gerstler

James Anthony Ruud

Shyh-Chin Huang

Mark Ernest Vermilyea

Wayne Charles Hasz

Robert John Zabala

Gregory Alan Steinlage

Ann Melinda Ritter

Eric Allen Ott

Thomas Robert Raber

Brian Magann Rush

Nicholas William Rathay

Michael Douglas Arnett

Robert Edward Schafrik

Sundeep Kumar

Mark Lawrence Hunt

Dalong Zhong

Thomas Carson Tiearney, Jr

Arthur Samuel Peck

Gregory Allen O'Neil

Anthony Joseph Vinciquerra

Eklavya Calla

Roger John Petterson

Gary J Shiflet

Timothy V Stotler

Dwight Eric Davidson

S Joseph Poon

Padmaja Parakala

Liqin Wang

Todd Charles Curtis

Theodore McCall Evenden

Thomas C Tiearney

Anand Krishnamurthy

Stephen Joseph Balsone

Sanjay Kumar Sondhi

Kivilcim Onal

Srinivasa Range Gowda

Chen Shen

Richard Didomizio

Joseph Poon

Sriparna Bhattacharya

Mahesh Chandran

Krishnamurhty Anand

Jr Michael Francis Xavier Gigliotti

Andrew John Elliot

Richard Didomizioo

A nickel-based braze alloy composition is described, including nickel, about 1 weight % to about 5 weight % boron (B); and about 1 weight % to about 20 weight % germanium (Ge). The composition is free of any silicon. Superalloy articles that contains a crack or other type of void or gap filled with the nickel-based braze alloy composition are also described, along with methods for filling such a gap. Related articles of manufacture and brazing processes to join metal components are also disclosed.

Amorphous ductile braze alloy compositions, and related methods and articles

A dual phase magnetic component, along with methods of its formation, is provided. The dual phase magnetic component may include an intermixed first region and second region formed from a single material, with the first region having a magnetic area and a diffused metal therein, and with the second region having a non-magnetic area. The second region generally has greater than 0.1 weight % of nitrogen.

Dual phase magnetic material component and method of its formation

Methods for forming a dual-phase magnetic component from an initial component comprising a non-magnetic austenite composition are provided. The method may include: forming a coating on a portion of the surface of the initial component to form a masked area while leaving an unmasked area thereon. Thereafter the initial component may be heated to a treatment temperature such that nitrogen diffuses out of the unmasked area of the initial component to transform the non-magnetic austenite composition to a magnetic phase in the unmasked area. Thereafter, the initial component may be cooled from the treatment temperature to form a dual-phase magnetic component having a magnetic region corresponding to the unmasked area and a non-magnetic region corresponding to the masked area.

Fabrication method for a component having magnetic and non-magnetic dual phases

A nickel-based braze alloy composition includes nickel, about 1 weight % to about 5 weight % boron (B); and about 1 weight % to about 20 weight % germanium (Ge). The composition is free of any silicon. Superalloy articles having a crack or other type of void or gap may be filled with the nickel-based braze alloy composition. Methods for filling such a gap are described.

A composition includes, by weight percent: Cobalt (Co) between about 4.5 and about 7.0; Chromium (Cr) between about 10.2 and about 11.5; Molybdenum (Mo) between about 0.5 and about 2.5; Tungsten (W) between about 4.0 and about 5.5; Rhenium (Re) between about 0 and about 1.2; Aluminum (Al) between about 6.2 and about 6.8; Tantalum (Ta) between about 4.5 and about 6.0; Titanium (Ti) between about 0 and about 0.5; Hafnium (Hf) between about 0 and about 0.5; Carbon (C) between about 0 and about 0.2; Boron (B) between about 0 and about 0.02; and the balance Nickel (Ni), and other incidental impurities.

Nickel-based superalloy

A high-temperature, high-strength, oxidation-resistant cobalt-nickel base alloy is disclosed. The alloy includes, in weight percent: about 3.5 to about 4.9% of Al, about 12.2 to about 16.0% of W, about 24.5 to about 32.0% Ni, about 6.5% to about 10.0% Cr, about 5.9% to about 11.0% Ta, and the balance Co and incidental impurities. A method of making an article having high-temperature strength, cyclic oxidation resistance and corrosion resistance is disclosed. The method includes forming a high-temperature, high-strength, oxidation-resistant cobalt-nickel base alloy as described herein; forming an article from the alloy; solution-treating the alloy by a solution heat treatment; and aging the alloy by providing at least one aging heat treatment at an aging temperature that is less than the gamma-prime solvus temperature, wherein the alloy is configured to form a continuous, protective, adherent oxide layer on an alloy surface upon exposure to a high-temperature oxidizing environment.

Cobalt-nickel base alloy and method of making an article therefrom

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. The leading edge assembly includes a plurality of structural layers and a plurality compliant layers alternately stacked with each other to facilitate thermal expansion and movement between the plurality of structural layers, while also providing a thermal break between the plurality of structural layers.

System for reducing thermal stresses in a leading edge of a high speed vehicle

Articles suitable for use in high temperature applications, such as turbomachinery components, and methods for making such articles, are provided. One embodiment is an article. The article comprises a material comprising a plurality of L12-structured gamma-prime phase precipitates distributed within a matrix phase at a concentration of at least 20% by volume, wherein the gamma-prime phase precipitates are less than 1 micrometer in size, and a plurality of A3-structured eta phase precipitates distributed within the matrix phase at a concentration in the range from about 1% to about 25% by volume. The solvus temperature of the eta phase is higher than the solvus temperature of the gamma-prime phase. Moreover, the material has a median grain size less than 10 micrometers.

Nickel alloy and articles

A composite composition that includes an MCrAlX alloy and a nano-oxide ceramic is disclosed. In the formula, M includes nickel, cobalt, iron, or a combination thereof, and X includes yttrium, hafnium, or a combination thereof, from about 0.001 percent to about 2 percent by weight of the alloy. The amount of the nano-oxide ceramic is greater than about 40 percent, by volume of the composition. A protective covering that includes the composite composition is also disclosed. The protective covering can be attached to a tip portion of a blade with a braze material. A method for joining a protective covering to a tip portion of a blade, and a method for repair of a blade, are also provided.

Composite composition for turbine blade tips, related articles, and methods

A cobalt-nickel base alloy is disclosed. The alloy includes, in weight percent: greater than about 4 % of Al, about 10 to about 20 % of W, about 10 to about 40 % Ni, about 5 to 20 % Cr and the balance Co and incidental impurities. The alloy has a microstructure that is substantially free of a CoAl phase having a B2 crystal structure and configured to form a continuous, adherent aluminum oxide layer on an alloy surface upon exposure to a high-temperature oxidizing environment. A method of making an article of the alloy includes: selecting the alloy; forming an article from the alloy; solution-treating the alloy; and aging the alloy to form an alloy microstructure that is substantially free of a CoAl phase having a B2 crystal structure, wherein the alloy is configured to form a continuous, adherent aluminum oxide layer on an alloy surface upon exposure to a high-temperature oxidizing environment.

Alumina-forming cobalt-nickel base alloy and method of making an article therefrom

Articles that include a material that has L1-structured gamma-prime phase precipitates within a matrix phase at a concentration of at least 20% by volume are disclosed. The gamma-prime phase precipitates are less than 1 micrometer in size. The material also has A3-structured eta phase precipitates distributed within the matrix phase at a concentration in the range from about 1% to about 25% by volume. The articles may be formed by mechanically working a workpiece that has at least about 40% nickel, about 1.5% to about 8% titanium, and about 1.5% to about 4.5% aluminum. The workpiece may be worked at a temperature below a solvus temperature of the eta phase; and then heat treated at a temperature sufficient to dissolve any gamma prime phase present in the workpiece but below the solvus temperature of the eta phase.

A method for making an article comprising a multilayered structure comprising a series of magnetic layers is provided. The method includes providing a substrate and depositing a series of magnetic layers on the substrate and disposing insulating layers between successive magnetic layers. Each magnetic layer has a thickness of at least about 2 micrometers and magnetic material has an average grain size less than 200 nm.

Magnetic laminated structure and method of making

An amorphous magnetic alloy is presented. The alloy has the general formula: (FeCo)MoPBCSi, wherein n is the atomic percent of iron and cobalt; x is the fraction of n; a, b, c, d and e are the atomic percent of molybdenum, phosphorous, boron, carbon and silicon respectively and n, x, a, b, c, d and e are defined by following relationship: 76&#x2266;n&#x2266;85; 0.05&#x3c;x&#x2266;0.50; 0&#x2266;a&#x2266;4; b&#x2267;10; 0&#x2266;c&#x3c;d; and 0.1&#x2266;e&#x2266;2. Articles comprising the alloy and methods employing the alloy for making articles are also presented.

Amorphous magnetic alloys, associated articles and methods

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Pazhayannur Ramanathan Subramanian