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

Claim 0:
1. 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; and
wherein the platform section is established between the airfoil section and a root section, the root section dimensioned to mount the airfoil to a rotatable hub, the airfoil section includes an internal wall extending inwardly from the tip portion with respect to the spanwise direction, and the airfoil section establishes an internal cooling arrangement comprising:
a flag cooling passage including a first section and a tip flag section, the first section extending in the spanwise direction from the root section, and the tip flag section extending in the chordwise direction along the tip portion from the first section to the trailing edge;
a serpentine cooling passage including a plurality of sections interconnected by one or more bends; and
the tip flag section and the serpentine cooling passage are situated on opposite sides of the internal wall relative to the thickness direction at a position aligned with the tip pocket relative to the chordwise direction.