Cooled blades for a gas turbine engine

摘要

An internally cooled turbine blade for a gas turbine engine is modified at the leading and trailing edge sections to include dynamic cool air flowing radial passageways 30 with an inlet 34 at the root and a discharge 36 at the tip, the passageways feeding a plurality of radially spaced film cooling holes 32 in the airfoil surface. Replenishment holes 38 radially spaced in the inner wall of the radial passageways communicate with internal cooling passages in the blade to replenish the cooling air lost to the film cooling holes. The discharge orifice is sized to match the backflow margin to achieve a constant film hole coverage throughout the radial length. Trip strips may be employed to augment the pressure drop distribution.