Airfoils with leading edge pockets for reduced heat transfer
AssigneeUnited Technologies Corporation
InventorsWilliam F. Lang, III, Thomas Alvin Auxier
Life of this patent
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Abstract
A gas turbine engine airfoil leading edge includes depressions therein longitudinally spaced apart and centered on stagnation points. The depressions stay filled with relatively stationary air during engine operation and reduce the heat load at the leading edge, which is primarily cooled by an internal supply of cooling fluid.
Claims11
An airfoil shaped article having a longitudinally extending leading edge and adapted to be disposed in a hot fluid medium flowing downstream relative thereto toward said leading edge, said article having a cooling fluid cavity therewithin proximate said leading edge for providing convective cooling of said leading edge, at least one depression formed in said leading edge defining a pocket of relatively stationary fluid therein for providing an insulating fluid layer between the hot flowing fluid and the article to reduce heat load at the leading edge.
An airfoil adapted for use in a gas turbine engine, said airfoil having a pressure surface, a suction surface, and a smoothly curved longitudinally extending leading edge blending with said pressure and suction surfaces, said airfoil having a cooling fluid cavity therewithin proximate said leading edge for providing convective cooling of said leading edge, said airfoil adapted to be disposed in a hot fluid medium flowing downstream relative thereto toward said leading edge, at least one depression formed in said leading edge defining a pocket of relatively stationary fluid therein for providing an insulating fluid layer between the hot flowing fluid and the article to reduce heat load at the leading edge.
Dependencies are inferred from the claim text.