| 摘要 |
An airfoil (18) for a gas turbine engine includes a generally radially- extending first cooling channel (40) disposed between pressure and suction sidewalls (20, 22 ) adjacent the leading edge (24) of the airfoil (18), and a generally radially - extending second cooling channel (40B) disposed aft of the first cooling channel (40A) . The second cooling channel (40B) is closed off at an outer end thereof and is disposed in fluid communication with a forward inlet (41) an inner end thereof. The firs t and second cooling channels (40A, 40B) are separated by a partition (38A) having a plurality of impingement holes (44) therein. A generally axially extending e nd channel (43) is disposed radially outward from the second cooling channel (40B) in fluid communication with the first cooling channel (40A) and with a dust hol e (46) disposed in the tip cap (34). The dust hole (46) is sized to permit the exit of debris entrained in a flow of cooling air from the airfoil (18).
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