Patent ID: 11905849
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, the airfoil comprising:
an airfoil body having a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge and defining a pressure side, and a suction side wall extending between the leading edge and the trailing edge and defining a suction side, wherein a plurality of cooling passages are formed within the airfoil body;
a leading edge cavity defined within the airfoil body and defined along the leading edge to provide cooling to the leading edge of the airfoil, wherein a leading edge interior rib defines an aft extent of the leading edge cavity;
a trailing edge cavity defined within the airfoil body and defined along the trailing edge to provide cooling to the trailing edge of the airfoil, wherein a trailing edge interior rib defines a forward extent of the trailing edge cavity;
a plurality of pressure side cavities defined by one or more pressure side skin cavity walls arranged along an interior surface of the pressure side wall, wherein at least one pressure side skin cavity wall does not extend to the suction side wall;
a plurality of suction side cavities defined by one or more suction side skin cavity walls arranged along an interior surface of the suction side wall, wherein at least one suction side skin cavity wall does not extend to the pressure side wall; and
a main body cavity extending between the leading edge interior rib and the trailing edge interior rib,
wherein the plurality of pressure side cavities and the plurality of suction side cavities are arranged in a staggered pattern in a direction from the leading edge to the trailing edge, with the one or more pressure side skin cavity walls, the one or more suction side skin cavity walls, the leading edge interior rib, and the trailing edge interior rib defining the bounds of the main body cavity,
wherein at least one of (i) a dimension of each pressure side cavity in a direction from the pressure side toward the suction side extends greater than 50% and less than 100% across the airfoil body and (ii) a dimension of each suction side cavity in a direction from the suction side toward the pressure side extends greater than 50% and less than 100% across the airfoil body.