| 摘要 |
An airfoil for a gas turbine engine includes a generally radially-extending first cooling channel disposed between pressure and suction sidewalls adjacent the leading edge of the airfoil, and a generally radially-extending second cooling channel disposed aft of the first cooling channel. The second cooling channel is closed off at an outer end thereof and is disposed in fluid communication with a forward inlet an inner end thereof. The first and second cooling channels are separated by a partition having a plurality of impingement holes therein. A generally axially extending end channel is disposed radially outward from the second cooling channel in fluid communication with the first cooling channel and with a dust hole disposed in the tip cap. The dust hole is sized to permit the exit of debris entrained in a flow of cooling air from the airfoil.
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