Siemens Energy Global Gmbh & Co. Kg

Ian T Doran

Jose L Rodriguez

Lara Richerson

Gary Brian Merrill

Wayne J McDonald

Douglas Bibb

Robert Bruce

Timothy Troyer

Andrew Belling

Scott Gangle

Christopher Duren

Louis Charles

Travis John Vitello

A method for producing a flexible tooling liner for casting a ceramic core is presented. The method includes the steps of producing a three-dimensional (3D) reference object representative of a ceramic core to be cast, disposing the reference object into a containment vessel configured to receive a liquid flexible tooling material, filling the containment vessel with the liquid tooling material so that the reference object is encapsulated by the liquid tooling material on the surface whose topography is intended to be imparted, allowing the liquid tooling material to cure, and separating the cured flexible tooling along a parting surface into opposing portions and removing the reference the reference object.

Method for producing flexible tooling for casting a ceramic core

A molding tool () for manufacturing cooling features in a ceramic core for a casting process includes a first mold portion () comprising a crossover hole forming feature (); a second mold portion () comprising an impingement jet receiving forming feature () for forming an impingement jet receiving feature having a desired aiming point (); and a sacrificial alignment member () for extending at least partially into the crossover hole forming feature () at least partially into the aiming point () of the impingement jet receiving forming feature () for substantially aligning a central axis () of the crossover hole forming feature () with the aiming point () to maintain a crossover hole and aiming point alignment during casting to ensure that the jet is directed at the aiming point () in a resultant cast part.

Manufacturing aligned cooling features in a core for casting

An airfoil for a turbine engine includes an array of pins positioned in an internal cavity of the airfoil, such that cooling channels are defined in the interspaces between adjacent pins. Each pin extends lengthwise from a first airfoil wall to a second airfoil wall and is connected thereto at a first intersection and at a second intersection respectively. The pin has a first cross-sectional shape at a respective intersection and a second cross-sectional shape at an intermediate plane located between the first and second intersections. The first cross-sectional shape includes a closed shape defined by relatively sharp corners and the second cross-sectional shape includes a closed shape defined by relatively rounded corners. A cross-sectional area of the pin at the intermediate plane is greater than a cross-sectional area of the pin at the respective intersection.

Airfoil for a turbine engine incorporating pins

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Charlottesville, VA, United States of America

Ian T Doran