An airfoil for a gas turbine engine, the airfoil comprising: an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge; a first core cavity within the airfoil body; a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body; wherein the first cavity wall has a chevron shape extending into the second core cavity and defines a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall; at least one first cavity impingement hole formed within the first surface, wherein the at least one first cavity impingement hole is configured to direct a first impingement flow from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall to form a first high momentum jet of impingement air thereon; at least one second cavity impingement hole formed within the second surface, wherein the at least one second cavity impingement hole is configured to direct a second impingement flow from the first core cavity through the at least one second cavity impingement hole to impinge upon the second exterior wall to form a second high momentum jet thereon; at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall; characterized in that: the airfoil further comprises a central ridge (742, 744) extending into the second core cavity from at least one of the first cavity wall and the second cavity wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber, the central ridge is a forward central ridge extending into the second core cavity from the first cavity wall, the airfoil further comprising an aft central ridge extending into the second core cavity from the second cavity wall. an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge; a first core cavity within the airfoil body; a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body; wherein the first cavity wall has a chevron shape extending into the second core cavity and defines a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall; at least one first cavity impingement hole formed within the first surface, wherein the at least one first cavity impingement hole is configured to direct a first impingement flow from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall to form a first high momentum jet of impingement air thereon; at least one second cavity impingement hole formed within the second surface, wherein the at least one second cavity impingement hole is configured to direct a second impingement flow from the first core cavity through the at least one second cavity impingement hole to impinge upon the second exterior wall to form a second high momentum jet thereon; at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall; characterized in that: the airfoil further comprises a central ridge (742, 744) extending into the second core cavity from at least one of the first cavity wall and the second cavity wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber, the central ridge is a forward central ridge extending into the second core cavity from the first cavity wall, the airfoil further comprising an aft central ridge extending into the second core cavity from the second cavity wall. the airfoil further comprises a central ridge (742, 744) extending into the second core cavity from at least one of the first cavity wall and the second cavity wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber, the central ridge is a forward central ridge extending into the second core cavity from the first cavity wall, the airfoil further comprising an aft central ridge extending into the second core cavity from the second cavity wall.