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

Claim 19:
20. 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; and
the airfoil including a plurality of sections longitudinally along the camber line;
wherein an angle between the camber line and a reference plane changes according to a slope as the airfoil extends longitudinally along the camber line;
wherein the slope along a first of the plurality of sections decreases as the first of the plurality of sections extends longitudinally along the camber line towards the trailing edge;
wherein the slope along a second of the plurality of sections increases as the second of the plurality of sections extends longitudinally along the camber line towards the trailing edge;
wherein 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; and
wherein the pressure side is concave as the airfoil extends longitudinally along the camber line from the leading edge to the trailing edge.