Unducted airfoil assembly
AssigneeGeneral Electric Company
InventorsKishore Ramakrishnan, Daniel Lawrence Tweedt
Life of this patent
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Abstract
An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
Claims20
An unducted airfoil assembly, comprising:
- an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges;
- and
- wherein a thickness of an airfoil section is defined as a distance measured between the pressure side and the suction side, and wherein the airfoil section comprises a maximum thickness, and wherein a chordwise fractional distance is defined from the leading edge of the airfoil section, and wherein the chordwise fractional distance to the maximum thickness of at least one airfoil section in a tip portion of the airfoil is less than 0.15.
An unducted airfoil assembly, comprising:
- an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges, and wherein the airfoil defines a pitch change axis;
- and
- wherein a position of a point on an airfoil section of the airfoil at the tip at a 0.25 chord fraction on a meanline of the airfoil section is such that a magnitude of a circumferential offset of the point from the pitch change axis is greater than a magnitude of an axial offset of the point from the pitch change axis.
An unducted airfoil assembly, comprising:
- an airfoil having a root, a medial portion, and a tip portion, the airfoil having spaced-apart pressure and suction sides extending radially in span from the root to a tip, and extending axially in chord between spaced apart leading and trailing edges;
- and
- wherein a thickness of an airfoil section is defined as a distance measured between the pressure side and the suction side, and wherein a thickness ratio of the airfoil section is defined as the thickness of the airfoil section divided by a maximum thickness of the airfoil section, and wherein the thickness ratio of at least one airfoil section in a tip portion of the airfoil is equal to or greater than 0.80 over a chord fraction range extending between:
- a first chord fraction location located midway between the leading edge and a second chord fraction location of the maximum thickness of the at least one airfoil section;
- and
- a third chord fraction location located midway between the trailing edge and the second chord fraction location.
Dependencies are inferred from the claim text.