General Electric Company

Charles Gitahi Mukira

Melvin Robert Jackson

Thomas Robert Raber

Mark Gilbert Benz

Gregory Alan Steinlage

Raymond Alan White

Gregory Reznikov

Aaron Todd Frost

Wayne Charles Hasz

Constantinos Minas

Shyh-Chin Huang

Canan Uslu Hardwicke

Ji-Cheng Zhao

Ann Melinda Ritter

William Scott Walston

John R Hughes

Adrian M Beltran

Thomas Martin Angeliu

Paul Vincent Crimi

Allan Richard Susi

Srikanth Chandrudu Kottilingam

Yan Cui

Jon Conrad Schaeffer

Thomas Joseph Kelly

Paul A Siemers

Mark Daniel Gorman

Douglas J Snyder

Liang Jiang

Richard John Grylls

Laurent Cretegny

Thomas Froats Broderick

Arthur Samuel Peck

Kevin S O'Hara

Warren Martin Miglietti

Clyde L Briant

Christopher Michael Penny

John Breunissen

James Michael Gent

Richard W Lindberg

Steven Charles Rauch

Ping Huang

Jiang Liang

Kevin Swayne O'Hara

A process for filling openings, including blind holes, through-holes, and cavities, in high temperature components. The process entails forming a powder mixture by mixing particles of at least a base alloy and a second alloy that contains a sufficient amount of a melting point depressant to have a lower melting temperature than the base alloy. The powder mixture is combined with a binder and compacted to form a compacted preform, which is then heated to remove the binder and form a rigid sintered preform. The sintered preform is produced, or optionally is further shaped, to have a cross-sectional shape and dimensions to achieve a clearance of up to 200 micrometers with the opening, after which the preform is placed in the opening and diffusion bonded within the opening to form a brazement comprising the particles of the base alloy dispersed in a matrix formed by the second alloy.

Process of filling openings in a component

A nickel-based braze composition is described, containing nickel, palladium, and restricted amounts of boron and silicon. The composition can also contain tantalum, titanium, and zirconium, as well as aluminum, chromium, and cobalt. A method for joining two metal components, using the braze composition, is also described. The braze composition can also be used to fill cracks or other cavities in a component, e.g., a gas turbine part formed from a nickel-based superalloy. Articles of manufacture which contain the braze composition are also described.

Nickel-based braze alloy compositions and related processes and articles

An alloy and a gas turbine engine component comprising an alloy are presented, with the alloy comprising:

Rhodium, platinum, palladium alloy

Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Repair of advanced gas turbine blades

A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Nickel-base superalloy composition and its use in single-crystal articles

An alloy and a gas turbine engine component comprising an alloy are presented, with the alloy comprising from about three atomic percent to about nine atomic percent of at least one precipitation-strengthening metal selected from the group consisting of zirconium, niobium, tantalum, titanium, hafnium, and mixtures thereof; from about one atomic percent to about five atomic percent ruthenium; and the balance rhodium; the alloy further comprising a face-centered-cubic phase and an L12&mdash;structured phase.

Rhodium-based alloy and articles made therefrom

A gas turbine airfoil and methods for manufacturing and repair of an airfoil, the airfoil comprising a wall, the wall defining the perimeter of the airfoil and comprising a leading edge section and a trailing edge section, wherein a majority of the surface area of the wall comprises a first material, the first material having an oxidation resistance and a melting temperature, and at least one portion of the wall comprises a second material, the second material having an oxidation resistance that is greater than the oxidation resistance of the first material and a melting temperature that is at least about 83 degrees Celsius (about 150 degrees Fahrenheit) greater than the melting temperature of the first material, the at least one portion of the wall located in at least one section of the wall selected from the group consisting of the leading edge section and the trailing edge section.

Airfoils with improved oxidation resistance and manufacture and repair thereof

An alloy comprising rhodium, aluminum, and chromium, wherein a microstructure of the alloy comprises a face-centered-cubic phase and a B2-structured phase and is essentially free of an L12-structured phase at temperatures greater than about 1000&deg; C., and a gas turbine engine component comprising the alloy.

High-temperature alloy and articles made therefrom

Superalloy weld composition and repaired turbine engine component

An alloy and repair material comprising the alloy, articles comprising the alloy and repair material, and methods for repairing articles including provision of the alloy as repair material are described, with the alloy comprising ruthenium, nickel, aluminum, and chromium, wherein a microstructure of the alloy is essentially free of an L1 -structured phase at temperatures greater than about 1000&deg; C. and comprises an A3-structured phase and up to about 40 volume percent of a B2-structured phase.

A process for the manufacture of repair material. The repair material is ductile and readily mechanically deformed and can be used in the repair of turbine components. The process comprises providing a directionally solidified material, cold-swaging the directionally solidified material, and heat treating the cold-swaged material into the repair material. The repair material, after the steps of cold-swaging and heat treatment, comprises a microstructure that is essentially free from cracks, for repairing the turbine component. The invention also sets forth methods for repair of articles, such as turbine components, using the repair material, and a turbine component repaired using the repair material.

Manufacture of repair material and articles repaired with the material

A brazed X-ray target includes a metallic cap and a graphite back including a nonlinear record groove attached thereto along a stepped surface. An upper corner joint of the stepped surface is distanced from a cap outer edge and a focal track where the maximum heat is generated during use of the target. The graphite back is extended outward toward the cap outer edge to increase a thermal storage of the graphite, and a recess is formed into the cap to maintain a selected moment of inertia of the target and thereby maintain the rotordynamics of a given X-ray tube.

High performance x-ray target

An improved X-ray tube target comprises a refractory metal target substrate and a refractory metal focal track applied to the target substrate by a tape casting process. The X-ray tube target comprises a refractory metal target substrate and a refractory metal focal track formed on the target substrate to form a focal track/target substrate interface plane that varies less than about &plusmn;0.13 mm.

X-ray target

An X-ray tube anode comprises a graphite ring, a target substrate applied onto the graphite ring and a target focal track applied onto the target substrate. The target focal track comprises a first refractory metal and the target substrate comprises a second refractory metal and at least one layer of a material that is characterized by characterized by a coefficient of thermal expansion (CTE) that is the same as the CTE of the target focal track or is intermediate between the CTE of the target focal track and the CTE of the substrate.

Composite X-ray target

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Clifton Park, NY, United States of America

Charles Gitahi Mukira