United Technologies Corporation

Ryan Shepard Levy

Bryan P Dube

Edward F Pietraszkiewicz

Richard H Page

Sandra S Pinero

Joel H Wagner

Eric A Grover

Mohamed Hassan

Takao Fukuda

Christopher B Jelks

Paul Thomas Rembish

Scott W Gayman

Robert L Hazzard

Domenico Valerio

Scott D Hartmann

Paul Smith

Stephen J Yee

Jesse Gannelli

Edward M Henrahan

The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.

Process and refractory metal core for creating varying thickness microcircuits for turbine engine components

A tool for forming a trench and a plurality of cooling holes within the trench includes a body, the body including a ridge portion extending along a first side of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.

Method of creating an airfoil trench and a plurality of cooling holes within the trench

A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.

Retrofit dirt separator for gas turbine engine

A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.

Turbine blade internal cooling configuration

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Middletown, CT, United States of America

Ryan Shepard Levy