A gas turbine engine component comprises: an airfoil (64; 138) having a wall that provides an exterior surface, a first cooling passage (94; 194) is arranged adjacent to and interiorly of the wall, a second cooling passage (96; 196) is arranged in the wall and provides a first fluid flow direction, a resupply channel (102; 202) is arranged in the wall and is fluidly interconnected to the second cooling passage (96; 196), a resupply hole (104; 204) fluidly interconnects the first cooling passage (94; 194) and the resupply channel (102; 202), the resupply channel (102; 202) is transverse relative to the second cooling passage (96; 196) to provide a second fluid flow direction that extends from the resupply hole (104; 204) to the second cooling passage (96; 196), wherein the second fluid flow direction extends from the resupply hole (104; 204) to the second cooling passage (96; 196) at an angle of less than 90 degrees relative to the first fluid flow direction, the airfoil (64; 138) includes multiple resupply channels (102; 202) spaced apart from one another and fluidly connected to the same second cooling passage (96; 196), the airfoil extends from a platform to a tip, and the exterior surface provides an exterior airfoil surface, the first fluid flow direction extending in a radial direction toward the tip, characterised in that: the resupply channel (102; 202) includes a first leg having a terminal end from which the resupply hole (104; 204) extends, and a second leg fluidly interconnects the first leg to the second cooling passage (96; 196), the first and second legs (112, 114) being canted relative to one another, wherein the first leg and the second cooling passage (96; 196) extend in the same direction, the second leg is at the angle relative to the second cooling passage (96; 196), first and second resupply channels (102; 202) are arranged on opposite lateral sides of the second cooling passage (96; 196), and the airfoil (64; 138) includes multiple second cooling passages (96; 196) each including multiple resupply channels (102; 202) and at least some of the multiple resupply channels (102; 202) of adjacent multiple second cooling passages (96; 196) interleaved with one another. an airfoil (64; 138) having a wall that provides an exterior surface, a first cooling passage (94; 194) is arranged adjacent to and interiorly of the wall, a second cooling passage (96; 196) is arranged in the wall and provides a first fluid flow direction, a resupply channel (102; 202) is arranged in the wall and is fluidly interconnected to the second cooling passage (96; 196), a resupply hole (104; 204) fluidly interconnects the first cooling passage (94; 194) and the resupply channel (102; 202), the resupply channel (102; 202) is transverse relative to the second cooling passage (96; 196) to provide a second fluid flow direction that extends from the resupply hole (104; 204) to the second cooling passage (96; 196), wherein the second fluid flow direction extends from the resupply hole (104; 204) to the second cooling passage (96; 196) at an angle of less than 90 degrees relative to the first fluid flow direction, the airfoil (64; 138) includes multiple resupply channels (102; 202) spaced apart from one another and fluidly connected to the same second cooling passage (96; 196), the airfoil extends from a platform to a tip, and the exterior surface provides an exterior airfoil surface, the first fluid flow direction extending in a radial direction toward the tip, characterised in that: the resupply channel (102; 202) includes a first leg having a terminal end from which the resupply hole (104; 204) extends, and a second leg fluidly interconnects the first leg to the second cooling passage (96; 196), the first and second legs (112, 114) being canted relative to one another, wherein the first leg and the second cooling passage (96; 196) extend in the same direction, the second leg is at the angle relative to the second cooling passage (96; 196), first and second resupply channels (102; 202) are arranged on opposite lateral sides of the second cooling passage (96; 196), and the airfoil (64; 138) includes multiple second cooling passages (96; 196) each including multiple resupply channels (102; 202) and at least some of the multiple resupply channels (102; 202) of adjacent multiple second cooling passages (96; 196) interleaved with one another.