General Electric Company

Polymet Corporation

Edward H Goldman

Ramgopal Darolia

Nicholas Damlis

James A Martus

William Scott Walston

David John Wortman

David F Lahrman

James R Dobbs

Anne M Isburgh

Robert D Field

Robert Daniel Lawrence

Dewayne Renaldo Davis

Steven Randolph Norris

William Charles Mosier

A method and fixture for filled billet packing wherein an entire pack is built up in a single step. Substantially even lateral forces are applied to wires and other elongated members within the billet by inserting filler rods at one or more places along the periphery of the pack.

Method and fixture for filled billet packing

A coated superalloy component includes a substrate article formed of a superalloy and an adherent coating over the substrate. The coating is a nickel-base superalloy containing 0.3 volume percent or more of a dispersed oxide of yttrium, hafnium and/or a rare earth, and, preferably, grain boundary strengthening elements such as carbon, zirconium, and boron. The oxide dispersoids improve the performance of the coating in service, reducing the incidence failures due to thermal fatigue, oxidation, and corrosion damage. The dispersoid-containing coating may be formed by directly depositing the oxide-containing coating, or by depositing a metallic coating under conditions which permit the formation of such dispersoids during the deposition process.

Superalloy component with dispersion-containing protective coating

A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with a radially extending airfoil having an outer wall surrounding at least one radially extending cavity and extending chordwise through at least a portion of the airfoil. The outer wall has ribs disposed on an inner surface of the outer wall and cooling passages formed between the outer wall and an insert disposed in the cavity against and in abutting sealing relationship with the ribs, wherein the outer wall is formed from two radially and chordwise extending sections, preferably suction and pressure side sections, bonded together while the insert was disposed inside the cavity. The insert provides an inner wall surrounding a hollow chamber generally conforming to the cavity the insert is disposed in and the insert includes a spring to force the inner wall out against the ribs during the bonding process.

Bonded turbine airfuel with floating wall cooling insert

A NiAl intermetallic alloy and article is provided with improved high temperature strength, particularly stress rupture strength, through the generation of a multiphase microstructure comprising a beta matrix and at least one precipitate phase. The strength properties and microstructure are the result of alloying with at least two elements selected from Ga, Hf, and optionally Ti, Zr, Ta, Nb, and V, in defined ranges. Preferred are at least two of the elements Ga, Hf, and Ti, and specifically preferred are all three. A specifically preferred form of the invention, in atomic percent, is about 45-59% Ni, about 0.02-0.5% Ga, about 0.2 to less than 1% Hf, about 0.1-10% Ti, with the balance A1 and incidental impurities.

NiAl intermetallic alloy and article with improved high temperature

A superalloy component includes a substrate article of a superalloy, and a strengthenable, adherent coating on the substrate. The coating is preferably a nickel-base superalloy that is strengthened by the formation of gamma and gamma-prime phases. The coating is stronger than conventional MCrAlX coatings, and, therefore, more resistant to thermal fatigue. One operable coating has a composition, in weight percent, of about 7.5 percent cobalt, about 9 percent chromium, about 6 percent aluminum, about 1 percent titanium, about 1.5 percent molybdenum, about 4 percent tantalum, about 3 percent tungsten, about 3 percent rhenium, about 0.5 percent hafnium, about 0.3 percent yttrium, about 0.5 percent columbium, about 0.05 percent carbon, about 0.015 percent boron, about 0.015 percent zirconium, and balance nickel.

Strengthened protective coatings for superalloys

An impinqement cooled airfoil is fabricated by diffusion bonding a pair of airfoil half-sections together using an insert which is prefabricated from diffusion bonding foil. The insert is perforated so as to act as an impingement baffle. Axially-extending ribs may be formed on the internal walls of the airfoil half-sections or on the insert to support and accurately space the insert member from the internal walls so as to optimize impingement cooling.

Impingement cooled airfoil with bonding foil insert

Cooling passages are accurately formed along the faying surfaces of a pair of diffusion bonded members such as a pair of half sections used to fabricate an airfoil. A particularly advantageous application of the invention is the photoetching of cooling air grooves into the opposed surfaces of a diffusion bonding foil used to form a diffusion bond between the faying surfaces of a trailing edge portion of a turbine blade or turbine vane. Such grooves may be made extremely small and in high numbers to promote efficient cooling of the trailing edge portions of these airfoils.

Photoetched cooling slots for diffusion bonded airfoils

There is provided by the present invention yttrium and yttrium-silicon bearing alloys which are chemically and mechanically compatible with advanced nickel-base superalloys and nickel-base eutectic superalloys and which posses excellent resistance to high temperature oxidation. The alloys of the invention are, therefore, particularly useful as a protective environmental coatings for the external surfaces of hot-stage aircraft gas turbine engine components, e.g., rotating blades and stationary vanes, made from such advanced superalloys.

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Cincinnati, OH, United States of America

Edward H Goldman