General Electric Company

General Electric Company Ge Aviation

John Matthew Powers

Warren Davis Grossklaus, Jr

Thomas Froats Broderick

William Clarke Brooks

Brian Dudley Dorrel

Jeffrey Allen Conner

Richard Roy Worthing, Jr

Lawrence Joseph Roedl

Jon Conrad Schaeffer

John Frederick Ackerman

William Randolph Stowell

Roger Dale Wustman

Eric Scott Huron

Evan Jarrett Dolley

Ian Thomas Goodall

David Edward Trider

Zeynep Bolukoglu

Doga Ulutas

Tugba Aydin

Methods for cleaning a superalloy substrate having engine deposits on its surface are provided. The method may include applying a permanganate solution onto the surface of the superalloy substrate, and applying a ferric chloride based cleaning composition onto the surface of the superalloy substrate. The ferric chloride based cleaning composition includes ferric chloride and at least one of nitric acid and phosphoric acid, such as within a solvent system (e.g., an aqueous solution including water).

Cleaning compositions and methods for removing oxides from superalloy substrates

A method for repairing a turbine blade for a gas turbine engine is provided. The method includes securing the blade into a clamping fixture, obtaining a zero reference from a gauging surface on the clamping fixture, coupling the clamping fixture to a grinding machine, and grinding the blade based on the zero reference.

Apparatus for rebuilding gas turbine engines

An undersize repair region of a gas turbine engine stationary shroud is repaired with a sufficient mass of a repair material. The repair region includes a protruding portion that is undersized, and the repair includes machining of the protruding portion, grooving the resulting rub surface, inserting a replacement element, applying a brazing repair material, and brazing the article to form a repaired article. The repair material preferably includes a first fraction of a first powder of a first alloy component, and a second fraction of a second powder of a second alloy component. The first alloy component and the second alloy component have different solidus temperatures. The repair material is placed in the repair region. The repair material and the repair region are heated to melt the repair material but not the repair region, and thereafter the repair material and the repair region are cooled to solidify the repair material.

Braze repair of shroud block seal teeth in a gas turbine engine

A method and cleaning composition for removing engine deposits from turbine components, in particular turbine disks and turbine shafts. This method comprises the following steps: (a) providing a turbine component having a surface with engine deposits thereon, wherein the turbine component comprises a nickel and/or cobalt-containing base metal; and (b) treating the surface of the turbine component with a cleaning composition to convert the engine deposits thereon to a removable smut without substantially etching the base metal of the turbine component. The cleaning composition comprises an aqueous solution that is substantially free of acetic acid and comprising: a nitrate ion source in an amount, by weight of the nitrate ion, of from about 470 to about 710 grams/liter; and a bifluoride ion source in an amount, by weight of the bifluoride ion, of from about 0.5 to about 15 grams/liter. The smut that is formed can be removed from the surface of the turbine component in a manner that does not substantially alter the surface thereof.

Composition for removing engine deposits from turbine components

An apparatus for aligning a gas turbine engine blade including an airfoil and a dovetail is provided. The apparatus includes at least one locator pin configured to engage a serration formed on the blade dovetail, a locator block supporting said locator pin where said locator block comprises at least one groove sized to receive said locator pin therein, and a slide block assembly for engaging a dovetail surface opposite the serration where said slide block assembly is configured to position the blade dovetail against said locator pin. The apparatus also includes a base member comprising a platform comprising an end plate, a bottom surface, and an opposite upper surface for supporting said slide block assembly and said locator block, said slide block assembly is slidably coupled to said platform upper surface, said platform upper surface defining a slotted opening extending through said bottom surface, said opening configured to receive the blade airfoil.

Apparatus for rebuilding gas turbine engine blades

Method for removing engine deposits from turbine components and composition for use in same

A fixture for holding a gas turbine engine blade having an airfoil extending outward from a shank and a dovetail extending inward from the shank for attaching the blade to a disk of the engine. The dovetail includes at least one pair of protrusions extending fore and aft along opposite sides of the blade. Each of the protrusions including a pressure face generally facing the airfoil of the blade for engaging the disk to retain the blade in the disk during operation of the engine. The fixture includes a support for receiving the dovetail and a clamp mounted adjacent the support for movement between a clamped position in which the clamp engages the dovetail to hold the dovetail against the support and a released position in which the clamp disengages the dovetail to permit removal of the blade from the fixture.

Fixture for holding a gas turbine engine blade

A method of repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method is particularly suited for completely removing a thermal insulating ceramic layer of thermal barrier coating system that includes a metallic bond coat, such as a diffusion aluminide or MCrAlY coating, between the surface of the component and the ceramic layer, while leaving the bond coat substantially undamaged. Furthermore, the method of this invention includes a technique by which ceramic material within cooling holes in the component can be removed without damaging the underlying bond coat. The process steps generally include removing the ceramic layer from the surface of the component by subjecting the ceramic layer to a caustic solution at an elevated temperature and pressure, and then removing ceramic material from the cooling hole by carefully directing a high-velocity fluid stream into the cooling hole. According to this invention, the high-velocity fluid stream is able to overcome the compressive stresses that otherwise anchor the ceramic in the cooling hole, yet does not remove or damage the bond coat underlying the ceramic.

Method for repairing a thermal barrier coating

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

A heating apparatus and method for welding a superalloy article. In a preferred embodiment, the apparatus and method entail welding a superalloy article within an enclosure equipped with a thermal radiation-generating device that preheats the article to a temperature of at least 1500.degree. F. prior to welding. The invention more particularly provides a thermally-reflective coating on a reflector member positioned adjacent the thermal radiation-generating device for the purpose of reflecting thermal radiation emitted by the device into the enclosure. The device is then operated to heat the superalloy article to a suitable temperature, e.g., 1500.degree. F. or more, after which a welding operation is performed on the superalloy article.

An apparatus and method for welding a superalloy article. The apparatus generally entails an enclosure adapted for containing a superalloy article, a polarity-reversing plasma transferred arc welder apparatus for welding a localized region of the article, an induction coil for heating the localized region, and elements for sensing and controlling the temperature of the localized region. The induction coil is placed in close proximity to the localized region of the article so that the temperature of the localized region is largely determined and quickly altered by the output of the coil. The polarity-reversing plasma transferred arc welding apparatus is operated at very low currents of not more than forty-five amps, so that the welding apparatus has only a secondary heating affect compared to the induction coil.

Welding method and apparatus therefor

An atmosphere controlled workpiece heating chamber includes a spaced apart multiple gas flow means combination which avoids contamination of the atmosphere within the chamber from ambient atmosphere such as air. In one form, the chamber includes a gas diffuser as one flow means, and a heating means, both of which are readily removable, and easily and accurately replaceable.

Growing community of inventors

Independence, KY, United States of America

John Matthew Powers