General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Brendon James Leary

David Wayne Weber

Gregory Thomas Foster

Michelle Jessica Iduate

Aaron Ezekiel Smith

Thomas Earl Dyson

Gregory Terrence Garay

Nicholas William Rathay

Gustavo Adolfo Ledezma

Jacob Charles Perry, Ii

Joseph Anthony Weber

Elisabeth Kraus Black

Michael James Healy

Felix Martin Gerhard Roerig

Thomas Etter

Lyndsay Marie Kibler

Tyler Christopher Henson

Julius Andreas Schurb

Joseph Block

Gary Michael Itzel

Zachary John Snider

Victor John Morgan

David Vincent Bucci

Sandip Dutta

Changjie Sun

Ananda Barua

Prabhjot Singh

Arvind Rangarajan

James Albert Tallman

Marc Edward Blohm

Ibrahim Sezer

Jeremy Peter Latimer

Sylvain Pierre

Dean Michael Robinson

Frederic Woodrow Roberts, Jr

Sathyanarayanan Raghavan

Jason Adam Neville

Patrick Daniel Noble

Robert Peter Hanet

Evan John Dozier

Earl Thomas Dyson

Joseph I Block

Frederic Woodrow Roberts Jr

Joseph Antony Weber

Jacob Charles Perry Ii

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

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

Flared central cavity aft of airfoil leading edge

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

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

Component with mechanical locking features incorporating adaptive cooling and method of making

An article of manufacture includes an article body portion (); at least one pedestal (A,A,) integrally formed with the article body portion (), and disposed at an outer periphery of (), and structurally coupled to the article body portion (); and at least one internal feature () disposed at least partially within the article body portion () and at least partially within the pedestal (A,A,). At least a portion of the internal feature () is hollow.

Additive supports with integral film cooling

A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.

Gas turbine component with ejection circuit for removing debris from cooling air supply

A method, medium, and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; execute an AM simulation on the model of the part to determine a prediction of thermal distortions to the part; execute a topology optimization (TO) to create TO supports that counteract the predicted thermal distortions; generate at least one rule-based support based on a geometry of the part to interface with the part at one or more regions other than the TO supports; combining the TO supports and the at least one rule-based support to generate a set of hybrid supports; save a record of the set of hybrid supports; and transmit the record of the set of hybrid supports to an AM controller to control an AM system to generate a support structure for an AM production of the part.

Hybrid support structures for additively printed parts

A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Turbine nozzle airfoil profile

A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.

Protective shields for improved coating of turbine component cooling features

An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall () enclosing an interior for the airfoil 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 airfoil to cool the tip of the airfoil.

Airfoil with tip rail cooling

Additive manufactured components including sacrificial caps, and methods of forming components including sacrificial caps are disclosed. The additive manufactured components may include a body portion including a first surface, and a feature formed in the body portion. The feature may include an aperture formed through the first surface of the body portion. Additionally, the components may include a sacrificial cap formed integral with at least a portion of the first surface of the body portion. The sacrificial cap may include a conduit in fluid communication with the feature. The sacrificial cap including the conduit may be removed from the body portion to expose the first surface and the aperture of the feature, respectively, after performing one or more post-build processes, such as shot peening, on the component and the sacrificial cap.

Additive manufactured components including sacrifical caps and methods of forming same

One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.

Turbine airfoil with trailing edge cooling circuit

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Simpsonville, SC, United States of America

Brendon James Leary