General Electric Company

Cory Michael Williams

Steven Robert Brassfield

Richard William Jendrix

Ching-Pang Lee

Mark Willard Marusko

Mark Edward Stegemiller

Roger Lee Doughty

Renee Solomon Wenstrup

Steve Mark Molter

An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.

Method and apparatus for cooling gas turbine rotor blades

An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.

Airfoil cooling circuits and method

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Maineville, OH, United States of America

Cory Michael Williams