General Electric Company

Steven Robert Brassfield

Gregory Terrence Garay

Zachary Daniel Webster

Tingfan Pang

Ching-Pang Lee

Weston Nolan Dooley

Daniel Endecott Osgood

Mark Edward Stegemiller

Matthew Lee Krumanaker

Aaron Ezekiel Smith

Robert Proctor

Larry W Plemmons

Shawn Michael Pearson

David R Linger

David A Di Salle

Aspi Rustom Wadia

Stephen Mark Molter

Helen Ogbazion Gabregiorgish

Xi Yang

Daniel Lee Durstock

James Michael Hoffman

Chander Prakash

Sean Robert Keith

Judd Dodge Tressler

Robert Frederick Bergholz

Richard William Jendrix

Hardev Singh

Alan L Webb

Cory Michael Williams

Ronald Scott Bunker

Jan Christopher Schilling

Kirk Douglas Gallier

Robert David Briggs

Brian Keith

Jonathan Russell Ratzlaff

Gunnar Leif Siden

Mark Willard Marusko

Kevin Robert Feldmann

Jonathan Philip Clarke

David Alan Frey

John Peter Heyward

Kevin Samuel Klasing

Jeremy Clyde Bailey

David Glenn Cherry

Wenfeng Lu

Michael Joseph Danowski

Paul Stuart Wilson

David John Humanchuk

George A Durgin

Roger Lee Doughty

James Harvey Laflen

Joseph M Guentert

William Charles Herman

Gerard Anthony Rinck

Peter Paul Pirolla

Baolan Shi

David Benjamin Helmer

Kelli Marie Fishback

Kurt Thomas Whittington

Nicholas Ertel

Vanessa Camarillo

Jonathan Filipa

Steve Mark Molter

Renee Solomon Wenstrup

Mark Edward Stegmiller

Daniel Endicott Osgood

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 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 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

The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.

Turbine engine component with baffle

A component, such as for a turbine engine, can include an airfoil with 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. The component can also include at least one cooling passage within the interior.

Turbine engine airfoil and method of cooling

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides 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, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

Engine component with set of cooling holes

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides 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, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

Engine component with cooling hole

An airfoil for a gas turbine engine can include an outer surface defining a pressure side and a suction side extending axially between a leading edge and a trailing edge and extending radially between a first end and a second end to define a span-wise direction, and a cooling circuit located within the airfoil. The cooling circuit can include a cooling air inlet passage, a radially extending supply passage, an upstream supply passage fluidly coupling the cooling air inlet passage and the supply passage, and a near wall cooling mesh extending along a portion of the outer surface.

Turbine blade

An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.

Component for a turbine engine with a conduit

An airfoil for a turbine engine can include an outer wall 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. A plurality of outlets and a plurality of scalloped portions can extend along the outer wall.

Turbine engine airfoil with a scalloped portion

An airfoil assembly for a turbine engine that includes a platform, a dovetail, an airfoil. The airfoil assembly can further include a cooling air circuit that fluidly connects to a platform cooling passage. The cooling air circuit and platform cooling passage can be contained within or housed at least in part by the platform, the dovetail, or the airfoil. The cooling air circuit can also include a deflector.

An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

Growing community of inventors

Cincinnati, OH, United States of America

Steven Robert Brassfield