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

Claim 15:
16. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section, wherein the compressor section is downstream from the fan section;
a geared architecture coupling the fan section to the turbine section;
an airfoil arranged in the compressor section and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has an axial stacking offset defined as a distance between a center of gravity for a particular span section and a reference point, the reference point corresponding to an axial center of one of a root of the airfoil or a rotor bore, a positive axial stacking offset being on an axially aft side of the reference point and a negative axial stacking offset being on an axially forward side of the reference point; 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.