General Electric Company

Nesim Abuaf

Ching-Pang Lee

Robert Alan Johnson

Wayne Charles Hasz

Ronald Scott Bunker

John Howard Starkweather

Ching Pang Lee

Melvin Robert Jackson

Ann Melinda Ritter

Steven George Goebel

Mark Gerard Rettig

Jon Conrad Schaeffer

Sanjay Chopra

Robert Patrick Campbell

Anthony J Loprinzo

Harmon Lindsay Morton

Steven Sebastian Burdgick

Gary Michael Itzel

Constantinos Minas

John R Hughes

Dean Thomas Lenahan

Iain Robertson Kellock

Adrian M Beltran

Victor H Correia

Jeremy Clyde Bailey

Francisco J Cunha

Kevin Joseph Barb

David Robert Schumacher

Paul Stuart Wilson

Sanjay M Correa

Steven Joseph Brzozowski

David M Kercher

Mitchell R Cohen

Douglas Arthur Lupe

Robert W Barito

Neil S Rasmussen

Francis Lawrence Kirkpatrick

Rong-Shi Paul Chiu

Brent A Gregory

Frederick Alan Buck

Kenneth L Downs

Samuel D Spring

Li-Chieh Szema

Mohammad Esmail Taslim

Paul Chiu

Myron Clyde Muth

Lance Gordon Peterson

Ross Anthony McLean

Jeffrey Alan Graves

Vincent Anthony Barry

Sankar Nellian

A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.

Method for providing turbulation on the inner surface of holes in an article, and related articles

An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.

Article having turbulation and method of providing turbulation on an article

A casting includes a heat transfer surface having a plurality of cavities. The plurality of cavities include a density of at least about 25 cavities per square centimeter to about 1,100 cavities per square centimeter resulting in increased surface area and therefore enhanced heat transfer capability. Also disclosed is a mold for forming a pattern for molding the casting. The mold includes a surface defining a portion of a chamber to which are attached a plurality of particles having an average particle size in a range of about 300 microns to about 2,000 microns.

Casting having an enhanced heat transfer, surface, and mold and pattern for forming same

The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.

Insert metering plates for gas turbine nozzles

A turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour and improve the heat transfer characteristics of the component. Methods for forming the turbine engine components are also disclosed.

Turbine engine component having enhanced heat transfer characteristics and method for forming same

A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

Method and apparatus for enhancing heat transfer in a combustor liner for a gas turbine

Castings for gas turbine parts exposed on one side to a high-temperature fluid medium have cast-in bumps on an opposite cooling surface side to enhance heat transfer. Areas on the cooling surface having defectively cast bumps, i.e., missing or partially formed bumps during casting, are thermally sprayed to provide a metallic cooling enhancement surface layer to salvage the part.

Method of salvaging castings with defective cast cooling bumps

A method of forming a turbine engine component, includes providing a mold having a textured region, pouring a molten alloy into the mold, and cooling the molten alloy to form a turbine engine component, wherein the turbine engine component has an enhanced surface area region corresponding to the textured region of the mold, the enhanced surface area region comprising randomly arranged bumps.

Method for forming a turbine engine component having enhanced heat transfer characteristics

A casting includes a heat tranfer surface having a pluality of cavities. The plurality of cavities includes a density of at least about 25 cavities per square centimeter to about 1,100 cavities per square centimeter resulting in increased surface area and therefore enhanced heat transfer capability. Also disclosed is a mold for forming a pattern for molding the casting. The mold includes a surface defining a portion of a chamber to which are attached a plurality of particles having an average particle size in a range of about 300 microns to about 2,000 microns.

A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.

Bucket platform cooling scheme and related method

Castings for gas turbine parts exposed on one side to a high-temperature fluid medium have cast-in bumps on an opposite cooling surface side to enhance heat transfer. Areas on the cooling surface having defectively cast bumps, i.e., missing or partially formed bumps during casting, are coated with a braze alloy and cooling enhancement material to salvage the part.

Salvaged castings and methods of salvaging castings with defective cast cooling bumps

An annular turbine shroud separates a hot gas path from a cooling plenum containing a cooling medium. Bumps are cast in the surface on the cooling side of the shroud. A surface coating overlies the cooling side surface of the shroud, including the bumps, and contains cooling enhancement material. The surface area ratio of the cooling side of the shroud with the bumps and coating is in excess of a surface area ratio of the cooling side surface with bumps without the coating to afford increased heat transfer across the element relative to the heat transfer across the element without the coating.

Enhanced heat transfer surface for cast-in-bump-covered cooling surfaces and methods of enhancing heat transfer

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Schenectady, NY, United States of America

Nesim Abuaf