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US 8,464,426 B2Granted
Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsJody Kirchner, Yuan Dong, Sanjay S. Hingorani
Life of this patent
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Abstract
A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.
Claims7
A method of designing an airfoil for a gas turbine engine, comprising the steps of:
- a) localizing a sweep angle at a leading edge of a tip region of the airfoil;
- and
- b) localizing a dihedral angle at the tip region of the airfoil, wherein the dihedral angle is applied by translating the airfoil in direction normal to a chord of the airfoil.
Dependencies are inferred from the claim text.