Dual-wall airfoil with leading edge cooling slot

A gas turbine engine, comprising:

• a compressor,
• a combustor, and
• a turbine section, wherein the turbine section includes a dual wall airfoil comprising a spar and a cover sheet, the spar including a cooling air plenum disposed along an airfoil axis, the cooling air plenum arranged to receive cooling air from the compressor, the dual wall airfoil comprising a pressure side, a suction side, and a leading edge, the spar including a plurality of standoffs along a pressure side and a leading edge wall each extending away from an outer surface of the spar, the standoffs extending in a direction traversing the leading edge wall, wherein at least a portion of the spar defines an inlet port in communication with the cooling air plenum, a suction-side panel coupled to the leading edge wall and spaced away from the spar, the suction-side panel including a leading end, and a pressure-side panel coupled to the standoffs, the standoffs extending between the spar and the pressure-side panel, the pressure-side panel including a leading end, the leading end of the pressure-side panel and the leading end of the suction-side panel defining a leading edge slot therebetween, wherein an outlet port is defined by an intersection of a pair of the standoffs and the leading edge slot, the outlet port in communication with the inlet port.