Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Wayne J McDonald

Ching-Pang Lee

Eric Joseph Schroeder

Jae Y Um

Zhengxiang Pu

Gerald L Hillier

Jan H Marsh

Matthew J Golsen

Erik Johnson

Anthony Waywood

Ian T Doran

Lara Richerson

Ralph W Matthews

Douglas Bibb

Robert Bruce

Andrew Belling

Mohamed Abdullah

Scott Gangle

Christopher Duren

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

The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures () defined by a plurality of radially-extending channel elements () and axially-extending passage elements () and a radially outer low flow framing channel element () located adjacent to a radially outer edge (). The core structure may be used for casting a gas turbine engine airfoil (). The radially outer framing channel element () comprises a plurality of notches () extending radially inwardly from the radially outer edge (). A distal portion () of the notches () overlaps in an axial direction with the rib-forming apertures () of a first axially-aligned outer row (). A radial height of at least one of a first and a second axially-extending passage element () is greater than a prevalent radial height of other axially-extending passage elements () in the core structure.

Turbine blade trailing edge with low flow framing channel

A core structure () includes a first core element () including a leading edge section (), a tip section (), and a turn section () joining the leading edge and tip sections (). The first core element () is adapted to be used to form a leading edge cooling circuit () in a gas turbine engine airfoil (). The leading edge cooling circuit () includes a cooling fluid passage () having a leading edge portion () formed by the first core element leading edge section (), a tip portion () formed by the first core element tip section (), and a turn portion () formed by the first core element turn section (). Each of the leading edge portion (), the tip portion (), and the turn portion () of the cooling fluid passage () are formed concurrently in the airfoil () by the first core element ().

Gas turbine airfoil including integrated leading edge and tip cooling fluid passage and core structure used for forming such an airfoil

An airfoil () for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more internal cavities () having an insert () contained therein that forms nearwall cooling channels () having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels () may be controlled via a plurality of cooling fluid flow controllers () extending from the outer wall () forming the generally hollow elongated airfoil (). The cooling fluid flow controllers () may be collected into spanwise extending rows (), and the internal cooling system () may include one or more bypass flow reducers () extending from the insert () toward the outer wall () to direct the cooling fluids through the channels () created by the cooling fluid flow controllers (), thereby increasing the effectiveness of the internal cooling system ().

Internal cooling system with insert forming nearwall cooling channels in midchord cooling cavities of a gas turbine airfoil

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Charlotte, NC, United States of America

Wayne J McDonald