Patent ID: 7377747

Claim:
An airfoil for a gas turbine engine having a longitudinal axis, said airfoil including a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls, and comprising: a generally radially-extending first cooling channel disposed between said pressure and suction sidewalls adjacent said leading edge; a generally radially-extending second cooling channel disposed aft of said first cooling channel, said second cooling channel being closed off at an outer end thereof and disposed in fluid communication with a forward inlet an inner end thereof; a generally radially extending partition having a plurality of impingement holes disposed between said first and second cooling channels; and a generally axially extending end channel disposed radially outward from said second cooling channel in fluid communication with said first cooling channel and with a first dust hole disposed in said tip cap, said first dust hole sized to permit the exit of debris entrained in a flow of cooling air from said airfoil.