United Technologies Corporation

Samuel D Draper

Brandon W Spangler

James Thompson Beals

Stephen Douglas Murray

Jose A Lopes

Bryan P Dube

Keith A Santeler

Jacob A Snyder

Michael K Turkington

Michael F Blair

William S Kvasnak

Abbas Alahyari

Stephen D Murray

Jacob B Snyder

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 turbine engine component, such as a blade or a vane, is provided by the present invention. The turbine engine component has a pressure side and a suction side. Each of the pressure and suction sides has an external wall and an internal wall. A first set of fluid passageways is located on the pressure side between the external wall and the internal wall. A second set of fluid passageways is located on the suction side between the external wall and the internal wall. Each of the fluid passageways in the first set and in the second set has a wavy configuration. The turbine engine component may also have one or more wavy trailing edge cooling passageways for cooling a trailing edge portion of the component.

Drillable super blades

An embedded microcircuit for producing an improved cooling film over a surface of a part, comprising an inlet through which a coolant gas may enter, a circuit channel extending from the inlet through which the coolant gas may flow, and a slot film hole formed at a terminus of the circuit channel through which the coolant gas may exit a part.

Film cooling for microcircuits

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

A linked microcircuit for providing coolant gas flow through an aircraft part, comprising at least one inlet through which a coolant gas may enter, a circuit channel extending from the at least one inlet through which the coolant gas may flow wherein the circuit channel is formed from the superimposition of a plurality of alternating serpentine circuits, and at least one outlet appended to the circuit channel through which the coolant gas may exit the circuit channel.

Growing community of inventors

Kohler, WI, United States of America

Samuel D Draper