Patent ID: 11905849
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 13:
14. A gas turbine engine comprising:
a turbine section;
a compressor section; and
an airfoil located in at least one of the turbine section and the compressor section, 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 the pressure side cavities and the suction side cavities extends in a direction between the suction side and the pressure side for a distance that is at least 50% of a span across the airfoil body.