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

Claim 13:
14. The gas turbine engine as recited in claim 9, wherein the platform section is established between the airfoil section and a root section, the root section dimensioned to mount the blade to a rotatable hub, 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 radial 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.