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US 12,618,329 B2Granted
Unducted airfoil assembly
AssigneeGeneral Electric Company
InventorsKishore Ramakrishnan, Daniel Lawrence Tweedt, Valeria Andreoli
Life of this patent
Estimating the term…
Abstract
An unducted airfoil assembly includes an airfoil defining a leading edge, a trailing edge, a root, and a tip. A forward-most axial point of the leading edge is radially located at or greater than sixty percent of a tip radius of the airfoil when the airfoil is oriented at a design orientation for subsonic cruise operation.
Claims12
An unducted airfoil assembly, comprising:
- an airfoil defining a leading edge and a trailing edge, a root and a tip;
- wherein a forward-most axial point of the leading edge is radially located between sixty percent and seventy-five percent of a tip radius of the airfoil when the airfoil is oriented at a design orientation for subsonic cruise operation, wherein the forward-most axial point of the leading edge is arcuate, wherein the forward-most axial point of the leading edge is unducted, wherein the unducted airfoil assembly is configured to generate a power loading between 80 hp/ft2 and 160 hp/ft2 at a cruise altitude during a cruise operating mode, wherein a maximum chord extending from the leading edge to the trailing edge is located at or greater than seventy-five percent of the tip radius, and wherein the maximum chord is configured to localize sweep in an acoustically sensitive portion of the airfoil.
An unducted airfoil assembly, comprising:
- an airfoil defining a leading edge and a trailing edge, and further defining a root and a tip, wherein the airfoil is oriented at a design orientation for subsonic cruise operation;
- and
- a maximum chord extending from the leading edge to the trailing edge is located at or greater than seventy-five percent of a tip radius of the airfoil, wherein the unducted airfoil assembly is configured to generate a power loading between 80 hp/ft2 and 160 hp/ft2 at a cruise altitude during a cruise operating mode, wherein the maximum chord is configured to localize sweep in an acoustically sensitive portion of the airfoil, wherein a forward-most axial point of the leading edge is arcuate, wherein the forward-most axial point of the leading edge is unducted.
Dependencies are inferred from the claim text.