General Electric Company

General Electric Technology Gmbh

Sandip Dutta

Gary Michael Itzel

Benjamin Paul Lacy

Srikanth Chandrudu Kottilingam

Matthew Troy Hafner

David Edward Schick

John McConnell Delvaux

Joseph Anthony Weber

James Zhang

Zachary John Snider

Stephen Paul Wassynger

Kassy Moy Hart

Jaime Javier Maldonado

David Wayne Weber

Joseph Leonard Moroso

Yan Cui

Brian Lee Tollison

Brendon James Leary

Xiuzhang James Zhang

Ibrahim Sezer

James William Vehr

Scott Francis Johnson

Peter Galen Stevens

Sean Patrick Gunning

John Mcconnell Delvaux

Lbrahim Sezer

Joseph Antony Weber

Joseph Moroso

At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

Turbine components and methods of manufacturing

The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

Impingement insert for a gas turbine engine

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

Turbine component and methods of making and cooling a turbine component

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.

Turbomachine rotor blade

An article and method of forming an article are provided. The article includes a body portion separating an inner region and an outer region, an aperture in the body portion, the aperture fluidly connecting the inner region and the outer region, and a baffle extending along at least a portion of an inner surface of the article, the baffle dividing the inner region into a plurality of sub-regions. The method of forming an article includes forming a body portion defining an inner region and an outer region, forming an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and forming at least one baffle extending along at least a portion of an inner surface of the body portion, the at least one baffle dividing the inner region into a plurality of sub-regions. Also provided is a component including a cooling article disposed therein.

Article, component, and method of forming an article

At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a mounting location of the turbine component in a turbine. Methods of manufacturing articles and turbine components are also disclosed.

Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.

Turbine components and method for forming turbine components

The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.

Turbomachine rotor blade pocket

A method of fabricating a component having active cooling with film holes and other exposed holes is provided. The method includes the step of providing a component including at least one aperture disposed on a surface of the component and fluidly connected to at least one fluid flow passage, the at least one aperture comprising a floor extending from the at least one fluid flow passage to the surface of the component, and a ceiling facing the floor. The method further includes the step of applying a thermal barrier coating over at least a portion of a substrate. The method further includes the step of removing a portion of the thermal barrier coating covering the at least one aperture. The method further includes the step of forming with an additive manufacturing method one or both of a sharp-edged hood of the at least one aperture and at least one feature disposed on the floor.

Component having active cooling and method of fabricating

An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.

Apparatus, turbine nozzle and turbine shroud

An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.

Impingement insert

Various geometries for a trailing edge cooling system for a turbine blade. The trailing edge cooling system may include a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the turbine blade. Each cooling circuit may include an outward leg extending axially toward the trailing edge, and a plurality of turn legs in fluid communication with the outward leg. The plurality of turn legs may be positioned adjacent the trailing edge. Each cooling circuit may also include a return leg positioned adjacent the outward leg and extending axially from the trailing edge. The return leg may include a first portion and a second portion. The first portion may have a first width, and a second may have a second width that is greater than the first width of the first portion.

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Greenville, SC, United States of America

Sandip Dutta