A turbine airfoil comprising: an outer wall delimiting an airfoil interior, the outer wall extending span-wise along a radial direction of a turbine engine and being formed of a pressure side wall and a suction side wall joined at a leading edge and a trailing edge, a plurality of partition walls positioned in the airfoil interior connecting the pressure and suction side walls (16, 18) along a radial extent, at least one elongated hollow body positioned between a pair of adjacent partition walls and comprising a radial cavity (T1, T2) therewithin, first and second connector ribs (32, 34) that respectively connect the elongated hollow body to the pressure side wall and the suction side wall along a radial extent, whereby a serpentine cooling path (60a, 60b) is formed, comprising an upstream radial flow pass (B,E) and a downstream radial flow pass (C, D) in serial flow relationship conducting a coolant in opposite radial directions, each radial flow pass (B, E/ C,D) comprising, in flow cross-section, a first near-wall cooling channel defined between the elongated hollow body and the pressure side wall, a second near-wall cooling channel defined between the elongated hollow body and the suction side wall, and a connecting channel defined between the elongated hollow body and a respective one of the partition walls, connecting the first and second near-wall cooling channels (72, 74), third and fourth connector ribs (92, 94) which respectively connect the elongated hollow body to the pressure and suction side walls (16, 18) along a radial extent, the third and fourth connector ribs (92, 94) being respectively spaced from the first and second connector ribs (32, 34) to define a first impingement volume and a second impingement volume, wherein the downstream radial flow pass (C, D) is fluidically connected to the radial cavity (T1, T2), whereby relatively heated coolant from the serpentine cooling path (60a, 60b) is directed into the radial cavity (T1, T2) to warm the elongated hollow body, and is subsequently discharged via impingement openings on the elongated hollow body into the first and second impingement volumes (102, 104) that respectively adjoin the pressure and suction side walls (16, 18), thereby reducing a temperature gradient between the elongated hollow body and the outer wall. an outer wall delimiting an airfoil interior, the outer wall extending span-wise along a radial direction of a turbine engine and being formed of a pressure side wall and a suction side wall joined at a leading edge and a trailing edge, a plurality of partition walls positioned in the airfoil interior connecting the pressure and suction side walls (16, 18) along a radial extent, at least one elongated hollow body positioned between a pair of adjacent partition walls and comprising a radial cavity (T1, T2) therewithin, first and second connector ribs (32, 34) that respectively connect the elongated hollow body to the pressure side wall and the suction side wall along a radial extent, whereby a serpentine cooling path (60a, 60b) is formed, comprising an upstream radial flow pass (B,E) and a downstream radial flow pass (C, D) in serial flow relationship conducting a coolant in opposite radial directions, each radial flow pass (B, E/ C,D) comprising, in flow cross-section, a first near-wall cooling channel defined between the elongated hollow body and the pressure side wall, a second near-wall cooling channel defined between the elongated hollow body and the suction side wall, and a connecting channel defined between the elongated hollow body and a respective one of the partition walls, connecting the first and second near-wall cooling channels (72, 74), third and fourth connector ribs (92, 94) which respectively connect the elongated hollow body to the pressure and suction side walls (16, 18) along a radial extent, the third and fourth connector ribs (92, 94) being respectively spaced from the first and second connector ribs (32, 34) to define a first impingement volume and a second impingement volume, wherein the downstream radial flow pass (C, D) is fluidically connected to the radial cavity (T1, T2), whereby relatively heated coolant from the serpentine cooling path (60a, 60b) is directed into the radial cavity (T1, T2) to warm the elongated hollow body, and is subsequently discharged via impingement openings on the elongated hollow body into the first and second impingement volumes (102, 104) that respectively adjoin the pressure and suction side walls (16, 18), thereby reducing a temperature gradient between the elongated hollow body and the outer wall.