Patent ID: 11867195
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 9:
10. An airfoil for a gas turbine engine comprising:
a pressure side and a suction side extending in a radial direction from a 0% span position to a 100% span position and in an axial direction between a leading edge and a trailing edge;
an axial stacking offset defined as a distance between a center of gravity for a particular span section and a reference point corresponding to an axial center of a root of the airfoil, a positive axial stacking offset being on a side of the reference point towards the trailing edge and a negative axial stacking being on a side of the reference point towards the leading edge; and
wherein the axial stacking offset at a 10% span position is positive and greater than or equal to an axial stacking offset at the 100% span position, and a maximum positive axial stacking offset value of the axial stacking offset across the 0% span position to the 100% span position of the airfoil is greater than an absolute value of any negative axial stacking offset at the 100% span position.