F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/18 (2006.01)
Patent
CA 2548339
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 first and second cooling channels (40A, 40B) are separated by a partition (38A) having a plurality of impingement holes (44) therein. A generally axially extending end 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 hole (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).
Company General Electric
Craig Wilson And Company
LandOfFree
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