General Electric Company

Ronald Scott Bunker

Ching-Pang Lee

Robert David Briggs

Don Mark Lipkin

Jason Randolph Allen

Scott Andrew Weaver

Jeremy Clyde Bailey

Bin Wei

Victor Hugo Silva Correia

Nesim Abuaf

Nirm Velumylum Nirmalan

Ann Melinda Ritter

Robert Charles Groves, Ii

Eric Richard Bonini

Gary Michael Itzel

Wayne Charles Hasz

Lawrence Bernard Kool

Andrei Tristan Evulet

Todd Garrett Wetzel

Dennis Michael Gray

Kevin Robert Feldmann

Jared Peter Buhler

John Brian McDermott

Brian Kenneth Corsetti

Raul Basilio Rebak

Narendra Digamber Joshi

Benjamin Paul Lacy

Shyh-Chin Huang

Kirk Douglas Gallier

Frederic Joseph Klug

Guanghua Wang

Chellappa Balan

Renee Bushey Rohling

Melvin Robert Jackson

Thomas Edward Johnson

Canan Uslu Hardwicke

Zachary Daniel Webster

Stanley Kevin Widener

Venkat Eswarlu Tangirala

Christian Lee Vandervort

Byron Andrew Pritchard

Kevin Richard Kirtley

William Paul Minnear

Gulcharan Singh Brainch

Shawn Michael Pearson

Wilbur Douglas Scheidt

Magdi Naim Azer

Timothy Deryck Stone

Wenwu Zhang

Shawn David Wehe

Ramgopal Darolia

William Thomas Carter

Jon Conrad Schaeffer

Marshall Gordon Jones

Mohamed Ahmed Hashish

Aaron Ezekiel Smith

Anthony John Dean

Steven Robert Brassfield

Ambarish Jayant Kulkarni

Robert Proctor

Krishan Lal Luthra

Robert Francis Manning

David Martin Johnson

Douglas Gerard Konitzer

Mohammed El Hacin Sennoun

Hsin-Pang Wang

Andrew Lee Trimmer

Adam Rasheed

Mark Eugene Noe

Steven J Craigen

Joel Meier Haynes

John R Hughes

Jonathan Russell Ratzlaff

Harvey M Maclin

Emil Donald Jarczynski

Erich Alois Krammer

Chander Prakash

Curtis Walton Stover

John Charles Intile

Gregory Michael Laskowski

David Michael Chapin

Francisco J Cunha

Thomas Tracy Wallace

Kenneth Neil Whaling

Kathleen Blanche Morey

Robert Frederick Bergholz

Steven Joseph Brzozowski

Scott Michael Carson

Satoshi Atsuchi

Louis Andrew Schick

George Charles Goodman

Paul H Tacheron

Douglas Ray Smith

James DeLancey

Susan Marie Hyde

Nicholas Damlis

Nishith Pramod Vora

Scott Henry Lamson

Robert Patrick Campbell

Emily Rosette Clark

A method of forming a passage in a turbine component includes: using an additive manufacturing process to form a first support structure on a first surface of the turbine component; forming a second support structure on a second surface of the turbine component, the second support structure being spaced apart from the first support structure; and forming a passage in the turbine component between the first and second support structures.

Additive manufacturing method for making holes bounded by thin walls in turbine components

An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.

Engine component with film hole

A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.

Trailing edge cooling for a turbine blade

A method of forming structure on a component includes: providing a component having a first surface; adhering powder to the first surface; and directing a beam from a directed energy source to fuse the powder in a pattern corresponding to a layer of the structure.

Additive manufacturing on 3-D components

An engine component can comprise a cooled surface adjacent to a cooling flow and a hot surface adjacent to a hot flow of fluid. The component can comprise a wall separating the hot and cooling flows, defining the cooled surface and the hot surface, and having a plurality of film holes disposed in the wall. At least one turbulator and at least one film hole inlet can be disposed on the cooled surface. The turbulator and the inlet can be arranged to provide a steady flow of cooling fluid to the film hole. One arrangement can comprise spacing the film hole inlet at least two turbulator heights from the turbulator.

Engine component with film cooling

A component is provided and includes a substrate comprising an outer and an inner surface, where the inner surface defines at least one hollow, interior space. The component defines one or more grooves, where each groove extends at least partially along the outer surface of the substrate and has a base and a top. The base is wider than the top, such that each groove comprises a re-entrant shaped groove. One or more access holes are formed through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. Each access hole has an exit diameter D that exceeds the opening width d of the top of the respective groove. The diameter D is an effective diameter based on the area enclosed. The component further includes at least one coating disposed over at least a portion of the surface of the substrate, wherein the groove(s) and the coating together define one or more re-entrant shaped channels for cooling the component. A method for manufacturing the component is also provided. A method for manufacturing a component is also provided, where the groove and the access hole(s) are machined as a single continuous process, such that the groove and the access hole(s) form a continuous cooling passage.

Components with cooling channels and methods of manufacture

A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

Fillet optimization for turbine airfoil

An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.

Impingement holes for a turbine engine component

Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replacement portion on the intermediate component to form a repaired airfoil. The replacement portion defines at least one trailing edge ejection slot.

Methods for repairing airfoil trailing edges to include ejection slots therein

An engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component.

Component for a turbine engine with a hole

An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

Airfoil with cooling circuit

A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing. Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.

CMC blade with internal support

Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

Engine components with impingement cooling features

An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Engine component assembly

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Niskayuna, NY, United States of America

Ronald Scott Bunker