초록 ▼

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 trans

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.

대표청구항 ▼

1. 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; andb) localizing a dihedral angle at the tip region of the airfoil, wherein the dihedral angle is applied by translating the airfoil in

1. 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; andb) 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. 2. The method as recited in claim 1, wherein the sweep angle is a forward sweep angle. 3. The method as recited in claim 1, wherein said step a) includes the step of: displacing a plurality of airfoil sections of the airfoil parallel to the chord relative to a base-line rotor blade design. 4. The method as recited in claim 1, wherein the dihedral angle is a positive dihedral angle. 5. The method as recited in claim 1, wherein said step b) includes the step of: displacing a plurality of airfoil sections of the airfoil tangentially to the chord relative to a base-line rotor blade design. 6. The method as recited in claim 1, comprising the step of: c) extending the sweep angle and the dihedral angle over a distance of the airfoil equivalent to about 10% to about 40% of a span of the airfoil. 7. The method as recited in claim 6, wherein said step c) includes the step of: extending the sweep angle and the dihedral angle from an outer edge of the tip region radially inward along a radial axis over a distance equal to about 10% to about 40% of the span.