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

Claim 8:
9. A gas turbine engine comprising:
a compressor section including a compressor;
a turbine section including a turbine coupled to the compressor;
wherein the turbine section includes an array of blades rotatable about a longitudinal axis and an array of vanes adjacent to the array of blades; and
wherein each blade of the array of blades comprises:
an airfoil section extending in a radial direction from a root 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;
a platform section between the root section and the tip portion relative to the radial direction;
wherein the tip portion includes a tip pocket and a tip shelf extending inwardly from the tip, and the tip pocket and tip shelf are established on opposite sides of a shelf wall;
wherein the tip pocket is bounded in the thickness direction between the shelf wall and a sidewall, the tip pocket extends in the radial direction from a pocket floor to the tip, a radial face of the sidewall slopes outwardly from a first position to a second position at the tip, the first position corresponds to a span position of the pocket floor relative to a radial axis extending in the radial direction, and an average of a slope of the radial face between the first and second positions is greater than or equal to 10 degrees.