General Electric Company

Kenneth Jay Moore

Scott Alan Schimmels

Donald George LaChapelle

Matthew Ryan Ferslew

Stephen Joseph Waymeyer

John Clisby Blanton

Thomas Joseph Lipinski

Seung-Woo Choi

Bradford Alan Tracey

Paul Joseph Kreitzer

Michael Everitt Isenberg

Thomas Ryan Wallace

Narendra Are

Benjamin Johannes Seppala

A gas turbine engine having a fluid transfer connection is provided. The gas turbine engine includes a first component configured to channel a flow of air from a portion of the gas turbine engine; a second component configured to receive the flow of air from the first component, wherein the first component and the second component are movable relative to one another; a sleeve portion disposed between the first component and the second component; and a spoolie device disposed within the sleeve portion, the spoolie device having elliptical shaped opposing ends, wherein the spoolie device bridges the first component and the second component to channel the flow of air from the first component to the second component.

Gas turbine engine with spoolie fluid transfer connection

An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.

Turbine engine airfoil assembly

A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.

Turbine frame cooling systems and methods of assembly for use in a gas turbine engine

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Hamilton, OH, United States of America

Kenneth Jay Moore