General Electric Company

Steve Mark Molter

Steven Robert Brassfield

Mark Willard Marusko

Mark Edward Stegemiller

Richard William Jendrix

Cory Michael Williams

Renee Solomon Wenstrup

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.

Growing community of inventors

Cincinnati, OH, United States of America

Steve Mark Molter