COMPRESSOR AIRFOIL

摘要

A compressor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip of the airfoil. A leading edge sweep angle is defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge. A leading edge dihedral angle is defined relative to the tangent to the airfoil and a vertical at the point on the leading edge. A ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1. A method of forming such airfoil is also presented.

主权项

1. A compressor airfoil in a gas turbine engine, the airfoil comprising:
opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending in a span direction from a root to a tip of the airfoil; a leading edge sweep angle defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge; a leading edge dihedral angle defined relative to the tangent to the airfoil and a vertical at the point on the leading edge; and a ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1.