General Electric Company

Thomas Froats Broderick

Andrew Philip Woodfield

John Matthew Powers

Eric Allen Ott

David Edwin Budinger

Richard Roy Worthing, Jr

Judson Sloan Marte

Warren Davis Grossklaus, Jr

Zhiwei Wu

Jeffrey Lynn Myers

Lawrence Joseph Roedl

Xiaobin Chen

Peter Wayte

Yanmin Li

David Henry Abbott

Melvin Robert Jackson

Jon Conrad Schaeffer

John Frederick Ackerman

Michael James Weimer

Todd Jay Rockstroh

Ian Francis Prentice

William Randolph Stowell

Reed Roeder Corderman

William Scott Walston

Clifford Earl Shamblen

Jeffrey Allen Conner

Roger Dale Wustman

Charles Gitahi Mukira

John Peter Heyward

Joshua L Miller

Seetha Ramaiah Mannava

Dale Robert Lombardo

Ronald Lance Galley

Todd Stephen Heffron

Roger Owen Barbe

Francois Laurent Giguere

Gregory Alan White

Reed Roy Oliver

Bernard Harold Lawless

Paul Raymond Phaneuf

Paul Moncelle

Nancy Ann Sullivan

Peter Brian Haley

William Francis Bergeron

Thomas Caudwell Straub

William Woodrow Shepherd

William Terrence Dingwell

William Andrew Sharp, Ii

Wesley Douglas Pridemore

Paul Robert Moncelle

William Andrew Sharp

David Henry Abbot

William Andrew Ii Sharp

A composition of matter is generally provided, in one embodiment, a titanium alloy comprising about 5 wt % to about 8 wt % aluminum; about 2.5 wt % to about 5.5 wt % vanadium; about 0.1 wt % to about 2 wt % of one or more elements selected from the group consisting of iron and molybdenum; about 0.01 wt % to about 0.2 wt % carbon; up to about 0.3 wt % oxygen; silicon and copper; and titanium. A turbine component is also generally provided, in one embodiment, that comprises an article made from a titanium alloy. Additionally, methods are also generally provided for making an alloy component having a beta transus temperature and a titanium silicide solvus temperature.

Titanium alloys and their methods of production

A method of manufacturing a three-dimensional target object may include forming a shell from loose machining powder using an additive manufacturing process and subjecting the shell to a densification process to form a target object. The shell may define an enclosure that contains additional machining powder. The densification process may include causing metallurgical bonding between the shell and additional machining powder contained in the enclosure defined by the shell and shrinking and/or distorting the shape of the shell to conform the target object to a three-dimensional model for the target object. The shell may include a plurality of layers and/or parts that differ at least in respect of density. The plurality of layers and/or parts may be configured based at least in part on the shrinking and/or distorting to the shape of the shell needed to conform the target object to the three-dimensional model for the target object.

Method for manufacturing objects using powder products

A method for manufacturing a three-dimensional part. The method includes: performing partial densification processing on loose machining powder, to form a densified and sealed enclosure, where there is still loose machining powder accommodated inside the enclosure; and performing overall densification processing on the enclosure and the machining powder inside the enclosure, so as to implement metallurgical bonding between the machining powder inside the enclosure and the enclosure during the densification, thereby forming a target three-dimensional part.

A titanium-alloy article is produced by providing a workpiece of an alpha-beta titanium alloy having a beta-transus temperature, and thereafter mechanically working the workpiece at a mechanical-working temperature above the beta-transus temperature. The mechanically worked workpiece is solution heat treated at a solution-heat-treatment temperature of from about 175&#xb0; F. below the beta-transus temperature to about 25&#xb0; F. below the beta-transus temperature, quenched, overage heat treated at an overage-heat-treatment temperature of from about 400&#xb0; F. below the beta-transus temperature to about 275&#xb0; F. below the beta-transus temperature, and cooled from the overage-heat-treatment temperature.

Method for producing a beta-processed alpha-beta titanium-alloy article

A metallic component, which may be an airfoil, includes at least one treated patch, wherein the entire thickness of the component within the treated patch is in a state of residual compressive stress. A surface-treated area overlaps at least a boundary between the treated patch and the remainder of the component. The surface of the component within the surface-treated area is in a state of residual compressive stress, so as to resist crack initiation at the boundary between the treated patch and the remainder of the component. A method is also provided for making such a component.

Fatigue-resistant components and method therefor

The present invention is a BLISK airfoil heat treating apparatus and method for heat treating the leading and/or trailing edge section(s) of a BLISK airfoil using the BLISK airfoil heat treating apparatus. The apparatus comprises a pair of hingedly connected heat treating shells, each shell having a cavity for receiving an airfoil edge section requiring heat treatment. A resistive heating element is positioned with the shells to heat the cavities.

Localized heat treating apparatus for blisk airfoils

A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and executing a brazing operation such that the airfoil vane is permanently coupled to the platform portion and such that the wear coating material is bonded across a predefined area of the platform.

Method for coating gas turbine engine components

A BLISK having a damaged blade, with a repair region that has a thickness less than a specified thickness as a result of damage during manufacture or prior service, is repaired by depositing repair metal onto the repair region to increase its thickness to greater than its specified thickness dimension. Only the repair region is stress relieved by heating the repair region to a stress-relieving temperature of from about 1150&#xb0; F. to about 1250&#xb0; F. for a time of at least about 1 hour. The intentional manipulation of microstructure in only the thinner airfoil sections allows multiple repairs, which are not possible in the thicker sections of the BLISK. An alpha-case thickness of repair metal, preferably of at least about 0.0002 inches of repair metal, is removed from a surface of the repair region.

Method for repairing a damaged blade of a Blisk

A metallic component is by at least one peripheral edge. The component includes at least one elongated treated zone having a length substantially greater than its width. This treated zone is spaced away from and disposed generally parallel to the peripheral edge of the component and the entire thickness of the component within the treated zone is in a state of residual compressive stress. Crack growth from the edge due to fatigue or damage is resisted.

A plurality of gas turbine components or other articles are manufactured from a plurality of metallic-alloy workpieces using a manufacturing apparatus having a metalworking apparatus, and an annealing apparatus wherein the individual workpieces are annealed by single-workpiece annealing and not by large-batch annealing. A workpiece flow of the plurality of workpieces is established sequentially through the metalworking apparatus and the annealing apparatus.

Method for manufacturing articles using a semi-continuous flow of workpieces through metal working and annealing apparatus

A method for laser shock peening an article including laser shock peening a first area with at least one high fluence laser beam and laser shock peening a border area between the first area and a non-laser shock peened area of the article with at least one first low fluence laser beam. The border area may be laser shock peened with a second low fluence laser beam or more low fluence laser beams wherein the second low fluence laser beam and others have a lower fluence than the first low fluence laser beam. The border area may be laser shock peened with progressively lower fluence laser beams starting with the one first fluence laser beam wherein the progressively lower fluence laser beams are in order of greatest fluence to least fluence in a direction outwardly from the first area through the border area to the non-laser shock peened area.

Lower fluence boundary laser shock peening

A method for heat treating titanium-alloy articles in a vacuum furnace includes a step of first determining, for a first set of titanium articles in a first vacuum furnace and for a first set of heat treatment conditions, a minimum surface area of the first set of titanium articles associated with an acceptable alpha case formation for the first set of titanium articles. There is a second determining, for a second set of titanium articles in a second vacuum furnace and for a second set of heat treatment conditions, of a minimum surface area of a second set of titanium articles associated with an acceptable alpha case formation for the second set of titanium articles, responsive to the value of the minimum surface area of the first set of titanium articles. There follows a heat treating of a third set of titanium articles in the second vacuum furnace and for the second set of heat treatment conditions, where the surface area of the third set of titanium articles is not less than the value of the minimum surface area of the second set of titanium articles.

Heat treatment of titanium-alloy articles to limit alpha case formation

A method is provided for making, from a plurality of members brazed together, an article including an environmental resistant surface coating and a wear resistant surface portion. Prior to brazing, the members are assembled with at least one preform including the wear resistant material in a matrix including a first brazing alloy having a brazing temperature in a brazing temperature range. The assembly of members includes a second brazing alloy having a brazing temperature in the brazing temperature range. The assembly of members and wear resistant preform is heated in the brazing temperature range to provide a brazed article preform. Then the article preform is machined to a selected geometry and can be coated with the environmental coating.

Method of making an environmental resistant brazed assembly including a wear resistant surface portion

Superalloy weld composition and repaired turbine engine component

A heating apparatus and method for welding a superalloy article. The apparatus and method of this invention provide for pre-weld and post-weld heat treatments to be performed on an article within the same enclosure in which the welding operation is performed. The apparatus accurately controls the temperature of the component to be welded throughout the temperature treatment profiles with the use of means for welding the article, means for heating the article, and means for sensing the article temperature. The apparatus also works in conjunction with a memory storage device that stores appropriate pre-weld and post-weld heat treatment temperature profiles and a welding temperature profile for the article.

Heating apparatus for a welding operation and method therefor

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Springboro, OH, United States of America

Thomas Froats Broderick