United Technologies Corporation

Jose A Lopes

Brandon W Spangler

James Thompson Beals

Stephen Douglas Murray

Samuel D Draper

Bryan P Dube

Keith A Santeler

Jacob A Snyder

Michael K Turkington

Michael D Greenberg

William Abdel-Messeh

Ricardo Trindade

Douglas E Duke

Andrew J Lutz

Eric Herbst

Aaron T Frost

Kevin J Pallos

Kenneth J Sawyer

Stephen D Murray

Jacob B Snyder

The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.

Enhanced turbine airfoil cooling

In accordance with the present invention, a casting system is provided which broadly comprises a core and a wax die spaced from said core, a refractory metal core having a first end seated within a slot in the core and a second end contacting the wax die for positioning the core relative to the wax die, and the refractory metal core having at least one of a mechanism for providing spring loading when closed in the wax die and a mechanism for mechanically locking the wax die to the core.

Refractory metal core wall thickness control

A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Investment casting core methods

A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Investment casting cores

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Ellington, CT, United States of America

Jose A Lopes