Blade with platform cooling

摘要

A cooled turbine blade for a gas turbine engine has a platform cooling supply channel 34 that supplies cooling air to a plurality of cooling holes 36 in the surface 28 of the blade platform 24 adjacent the trailing edge 22 of the blade. The passage 34 extends between the sides 30, 32 of the blade platform 24 and communicates with feather seal slots 42, 44 provided on the blade platform.