Patent ID: 11913353
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 15:
16. An airfoil for a gas turbine engine comprising:
a platform section;
an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip, the airfoil section having an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides spaced apart in a thickness direction between the leading edge and the trailing edge;
wherein the tip portion includes a tip pocket and a tip shelf extending inwardly from the tip, the tip pocket and tip shelf on opposite sides of a shelf wall, and the shelf wall has a serpentine profile;
wherein the tip pocket is bounded in the thickness direction between the shelf wall and a sidewall, the tip pocket extends in the spanwise direction from a pocket floor to the tip, and a radial face of the sidewall slopes outwardly from a first position to a second position at the tip, the first position corresponding to a span position of the pocket floor relative to the spanwise direction; and
wherein a bow angle is established between the first position and the second position relative to an axis extending in the spanwise direction, and the bow angle is greater than or equal to 10 degrees.