General Electric Company

Stephen Joseph Ferrigno

Melvin Robert Jackson

Seetharamaiah Mannava

Ching-Pang Lee

David Edwin Budinger

William D Cowie

Wayne Alan Demo

Bernard Patrick Bewlay

Bin Wei

Lawrence Bernard Kool

Nripendra Nath Das

Mark Alan Rosenzweig

Howard John Farr

Jerry Donald Schell

Jim D Reeves

Ronald Lance Galley

Gary Edward Trewiler

William R Young

Paul J Monson

Richard Patrick Chesnes

Michael Glenn Gordon

Tris Colaizzi

James Anthony Ruud

Thomas Joseph Kelly

Curtis Alan Johnson

Ji-Cheng Zhao

Mark Daniel Gorman

Ann Melinda Ritter

Timothy Joseph Trapp

Ralph James Carl, Jr

Warren Davis Grossklaus, Jr

Dennis Joseph Dalpe

Wendy Howard Murphy

Matthew J Stewart

James Edwin Rhoda

Robert George Zimmerman, Jr

James Douglas Risbeck

John Robert LaGraff

Herbert Halila

Albert E McDaniel

Leo Spitz MacDonald

Kevin G McAllister

Robert Dzugan

Gregory Christopher Firestone

Melvin Howard Wilkins

Alistair Smith

L Timothy Rasch

Thomas Edwin Anderson

David C Fairbourn

Marc J Froning

Thomas J Kelley

Michel Joseph Shaw

Brian Robert Graham

Mark Somerville

Michael J Shaw

Leo S Macdonald

John R Lagraff

Robert G Zimmerman

Matthew Stewart

A method for bonding airfoil sections includes aligning upper and stub airfoil sections having upper airfoil pressure and suction sides and stub airfoil pressure and suction sides respectively, pressing together upper and stub airfoil cross sections at upper and stub airfoil distal ends of the upper and stub airfoil sections respectively, and then resistance welding, preferably solid state resistance welding, the upper and stub airfoil sections together along the upper and stub airfoil cross sections by passing electrical current across the upper and stub airfoil cross sections. The upper and stub airfoil sections may be clamped between pressure and suction side upper airfoil electrodes and between the stub airfoil pressure and suction sides respectively. The method may be performed while the stub airfoil section is attached to an airfoil carrier such as a rotor disk rim, a gas turbine engine drum, or a gas turbine engine blade platform.

Solid state resistance welding for airfoil repair and manufacture

A method for restoring a length of at least one of a master rod and an articulating rod, the method including determining a length of the rod, if the rod is within an acceptable length, cleaning the rod, applying a masking material to a part of the rod to be protected, grit blasting the part of the rod not protected by the masking material, and applying a thermal spray to the part of the rod not protected by the masking material to increase the length of the rod.

Method, computer software code, and system for restoration of master and articulating rods

An electrochemical process for selectively stripping at least one coating from the surface of a substrate is disclosed. The substrate (often a turbine engine component) is immersed in a composition through which electrical current flows. The composition includes a halide salt, such as sodium chloride, ammonium chloride, and potassium chloride. In preferred embodiments, the electrical current is direct current (DC). The process is especially useful for selectively removing portions of diffusion aluminide coatings. For example, the additive layer can efficiently be removed, without substantially affecting the underlying diffusion layer or substrate. Related stripping compositions and apparatuses are also described.

Method for partially stripping a coating from the surface of a substrate, and related articles and compositions

A process for removing aluminosilicate-based material (e.g., 'CMAS') from a substrate is described. The material is treated with an aqueous composition containing at least one acid having the formula HAF, in which A is Si, Ge, Ti, Zr, Al, and Ga; and x is 1-6. Treatment of the substrate is often carried out by immersion in an aqueous bath. The process is also very effective for removing CMAS-type material from cavities in the substrate, e.g., cooling holes in a gas turbine component. Related compositions are also described.

Process for removing aluminosilicate material from a substrate, and related compositions

An internal coating on an internal passage wall exposed at a passage opening through an article external surface is protected from removal during repair of the article, including removal of at least a portion of an external coating, by a masking assembly disposed about the passage opening. The masking assembly comprises a masking member and a substantially flexible seal, substantially inert to a coating removal medium for the external coating. The masking member is shaped for disposition about the passage opening across a gap between the external surface and the masking member. The substantially flexible seal is disposed across the gap substantially to seal the gap.

Apparatus for retaining an internal coating during article repair

A protected article includes a nickel-base superalloy substrate, an interlayer overlying the substrate, and a protective layer overlying the interlayer. The protective layer has a composition comprising at least one of rhodium, platinum, palladium, and ruthenium. In one composition, palladium is present in an amount of from about 1 to about 41 atomic percent; platinum is present in an amount of about (40+atomic percent palladium) atomic percent for palladium ranging from about 1 atomic percent to about 14 atomic percent and up to about 54 atomic percent for palladium ranging from about 15 atomic percent up to about 41 atomic percent; rhodium is present in an amount of at least about 24 atomic percent; zirconium, hafnium, titanium, and mixtures thereof are present in an amount of from zero up to about 5 atomic percent; and ruthenium is present in an amount of from zero up to about 5 atomic percent, balance impurities. The interlayer has a coefficient of thermal expansion intermediate between that of the substrate and that of the protective layer. The protected article is fabricated by furnishing the substrate, applying the interlayer over the substrate, and applying the protective layer over the interlayer. The application of the protective layer may be, for example, by welding or attachment of a solid piece.

Article with intermediate layer and protective layer, and its fabrication

An airfoil body having a first wall including a plurality of ribs. An outer wall formed of a high temperature foil is attached to the ribs so as to form a plurality of channels. The first wall is protected from hot flowpath gases by the outer wall and by cooling air flowing through the channels.

Foil formed structure for turbine airfoil

A wall structure for a gas turbine engine component is provided which comprises a wall having a first side facing a flow of hot gases and a second side exposed to a source of cooling fluid. The wall has a plurality of holes formed therethrough, and an outer layer disposed on the first side. The holes greatly increase the wetted surface area of the wall exposed to cooling flow.

Foil formed cooling area enhancement

A turbine airfoil is provided having an integral tip cap and a pair of tip walls which extend radially outward past the tip cap to form a squealer tip. A coaxial pair of first and second holes extend through the tip cap and one of the tip walls respectively at an acute inclination angle, with the first hole being disposed so as to direct impingement cooling air on the tip wall having the second hole. A protective layer comprising a high temperature foil is disposed on the tip wall having the second hole therein.

Foil formed structure for turbine airfoil tip

An electrochemical stripping method for selectively removing at least one coating from the surface of a substrate is described. The substrate is immersed in an aqueous composition through which electrical current flows. The composition includes an acid having the formula H AF , in which &ldquo;A&rdquo; is Si, Ge, Ti, Zr, Al, or Ga; and x is 1-6. Various coatings can be removed, such as diffusion or overlay coatings. The method can be used to fully-strip a coating (e.g., from a turbine component), or to partially strip one sublayer of the coating. Related processes and an apparatus are also described.

Method and apparatus for selectively removing coatings from substrates

There is provided a turbine airfoil having a plurality of pressure side bleed slots through which cooling air is discharged. A portion of the slot openings are covered with an outer wall which comprises a high temperature foil.

Foil formed structure for turbine airfoil trailing edge

A method of cleaning airfoils and related turbine engine components that have a crust-like debris deposited on the surface thereof. This method involves subjecting at least the portion of the component having the deposit of the crust-like debris to sufficient laser shock peening to cause the debris on the surface thereof to be loosened therefrom so that the loosened debris can be removed from the component. This loosened debris can then be removed from the component, such as by passing a cleaning fluid through the portion of the component that is subjected to the laser shock peening.

Method of cleaning turbine component using laser shock peening

Method and apparatus for retaining an internal coating during article repair

The present invention includes a method of repairing an annular metallic article and the repaired article itself which has an axially extending annular support and a projection generally radially extending therefrom. The projection has an associated operating radial height as measured from a radially facing annular first surface of the support and an associated shape. An upper portion of the projection is removed forming a stub extending away from the first surface and having a bonding surface at a stub end spaced apart from the first surface. A metallic material is metallurgically bonded to the bonding surface forming an annular heat affected zone in the stub bounded by the bonding surface. A first portion of the metallic material is removed to restore the projection to the operating height and shape. At least one annular outer surface of the tooth extending over at least a portion of the heat affected zone is laser shock peened, preferably after the first portion of the metallic material is removed. A tip of the stub formed by the removing of the first portion of the metallic material may also be laser shock peened as may a non-heat affected zone portion of the stub extending at least a partial length of a distance from the heat affected zone to the first surface. Opposite forward and aft facing annular surfaces of the projection may be laser shock peened, preferably simultaneously. The laser beam may be fired normal to or at an oblique angle to the forward and aft facing annular surfaces.

Laser shock peened gas turbine engine seal teeth

A Ni-base alloy composition comprises of Zr, B, and Si. Zr and B are coupled to each other to form ZrB,, the B and Zr suppress melting points of the Ni-base alloy composition. Further, a Ni-base alloy composition also comprises Cr, Ti, and Ni, where the Ti and Cr suppress melting points.

Repair alloy compositions

Growing community of inventors

Cincinnati, OH, United States of America

Stephen Joseph Ferrigno