Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsJody Kirchner, Yuan Dong, Sanjay S. Hingorani
Life of this patent
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Abstract
A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.
Claims20
A blade for a gas turbine engine, comprising:
- a platform;
- an airfoil that extends from said platform, said airfoil extending in span between a root and a tip region and in chord between a leading edge and a trailing edge;
- a sweep angle defined at said leading edge;
- a dihedral angle defined relative to said chord of said airfoil;
- and
- said sweep angle and said dihedral angle localized at said tip region and extending over a distance of said airfoil equivalent to about 10% to about 40% of said span.
A gas turbine engine, comprising:
- a shroud assembly;
- a blade at least partially surrounded by said shroud assembly;
- said blade having an airfoil extending in span between a root and a tip region and in chord between a leading edge and a trailing edge, said airfoil including a sweep angle defined at said leading edge and a dihedral angle defined relative to said chord;
- and
- said sweep angle and said dihedral angle are localized at said tip region of said airfoil.
Dependencies are inferred from the claim text.