Patent ID: 11873730
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 15:
16. An apparatus for a gas turbine engine, comprising: an airfoil extending spanwise along a span line from a base to a tip, the airfoil extending laterally between a pressure side and a suction side, and the airfoil extending longitudinally along a camber line from a leading edge to a trailing edge;
wherein an angle from the camber line to a reference plane changes according to a slope as the airfoil extends longitudinally along the camber line;
wherein the slope has a first inflection point disposed at a location beyond ten percent of a distance longitudinally along the camber line from the leading edge to the trailing edge; and
wherein at least one of
an entirety of the suction side is convex as the airfoil extends longitudinally along the camber line from the leading edge to the trailing edge; or
an entirety of the pressure side is concave as the airfoil extends longitudinally along the camber line from the leading edge to the trailing edge.