General Electric Company

Ge Infrastructure Technology, LLC

Gregory Terrence Garay

Zachary Daniel Webster

Tingfan Pang

Daniel Endecott Osgood

Douglas Gerard Konitzer

Xi Yang

Steven Robert Brassfield

Brian David Przeslawski

Aaron Ezekiel Smith

Michael Scott Cole

Kirk Douglas Gallier

Michael A Brown

Ryan Christopher Jones

William Thomas Carter

Nicholas William Rathay

Mark Kevin Meyer

Daniel Lee Durstock

David Wayne Weber

Brendon James Leary

Thomas Earl Dyson

Gustavo Adolfo Ledezma

Kevin Robert Feldmann

Matthew Thomas Beyer

Helen Ogbazion Gabregiorgish

Douglas Ray Smith

Matthew Mark Weaver

Mark Willard Marusko

Bruce Clark Busbey

Michael John McCarren

James Herbert Deines

Brian Patrick Peterson

Ricardo Caraballo

Michael Brown

Michael John Mccarren

Meredith Elissa Dubelman

Brian Keith

Joseph Edward Hampshire

Weston Nolan Dooley

James Michael Hoffman

Randall Charles Bauer

Drew Michael Capps

Yoon Seok Choi

William Charles Herman

James Robert Bailey

Daniel Endicott Osgood

Nicole Barba

A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.

Turbomachine cooling trench

A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.

Component for a turbine engine with a cooling hole

A method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a filter, first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may manufactured using an additive manufacturing process and may include an integrated ceramic filter. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

Additively manufactured casting core-shell mold and ceramic shell with variable thermal properties

A method is provided for casting a component. Accordingly, data indicative of at least one location of a unitary core-shell mold which is susceptible to a stress concentration is received. An additive manufacturing process is employed to form the unitary core-shell mold defining a casting cavity. The unitary core-shell mold includes a shell wall defining an outer component shape and a core wall positioned inward of the shell wall. The core wall defines an inner component shape. The core wall and/or the shell wall defines at least one reinforcement recess adjacent to the at least one location which is susceptible to the stress concentration. Following the forming of the unitary core-shell mold, at least one support member is positioned within the reinforcement recess in contact with the at least one location. With the support member in place, the component is cast within the casting cavity.

Methods for casting a component via a unitary core-shell mold

A method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a first core portion, a first shell portion, and a second shell portion, wherein the first shell portion is adapted to interface with at least the second shell portion to form at least one first cavity between the core portion and the first and second shell portions. The core-shell mold may be inspected and assembled prior to connection of the wax gate component. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

Additively manufactured interlocking casting core structure with ceramic shell

An engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The apparatus formed from a method including calculating a factor and adjusting a variable until the factor is between a given range.

Engine component with structural segment

An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.

Blade with tip rail cooling

An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Airfoil tip rail and method of cooling

A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

Partial integrated core-shell investment casting molds that can be assembled into complete molds are provided herein. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. Core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold are also provided herein.

Method for making an integrated core-shell structure

A method of using additive manufacturing to form or print a component based on an original model of a component, where the geometry of the original model is compensated to form a compensated model. The compensated model can be used to form or print the component. The printed component as a final model can then be compared to the original model.

Compensation for additive manufacturing

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

Blade with tip rail, cooling

An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

Turbine engine airfoil

A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.

Gas turbine engines and methods associated therewith

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West Chester, OH, United States of America

Gregory Terrence Garay