General Electric Company
Turbine engine with component having a cooled tip

Abstract:

An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes a first cooling circuit having a first portion and a first tip portion and a second cooling circuit having a second portion and a second tip portion.