Compressor airfoil
First Claim
1. A compressor airfoil for 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 at all points along the span direction from the root to the tip.
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Accused Products
Abstract
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.
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Citations
18 Claims
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1. A compressor airfoil for a gas turbine engine, the airfoil comprising:
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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 at all points along the span direction from the root to the tip. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. A method of forming a blade having opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction side extending in a span direction from a root to a tip, the method comprising:
forming an airfoil having a ratio of a leading edge sweep angle to a leading edge dihedral angle being smaller than 1, the leading edge sweep angle defined between a tangent to the airfoil and flow velocity vector at a point on the leading edge, and the leading edge dihedral angle being defined between the tangent to the airfoil and a vertical at the point on the leading edge the ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1 at all points along the span direction from the root to the tip. - View Dependent Claims (18)
Specification