Airfoil having internal hybrid cooling cavities

A core structure for manufacturing an airfoil for a gas turbine engine, the core structure comprising:

• a first core cavity core to form a first core cavity;
• and
• a second core cavity core to form a second core cavity, the second core cavity core provided adjacent the first core cavity core, wherein the second core cavity core is arranged to form 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 in a formed airfoil body such that the first cavity wall is provided between the second core cavity core and the first core cavity core and the first and second exterior walls are exterior walls of the formed airfoil body;
• wherein a space between the first core cavity core and the second core cavity core that defines the first cavity wall includes a first portion to form a first surface of the first cavity wall that is angled toward the formed first exterior wall and a second portion to form a second surface of the first cavity wall that is angled toward the formed second exterior wall, wherein the space that defines the first cavity wall has a chevron shape extending into the second core cavity core;
• at least one first cavity impingement stem extending between the first core cavity core and the second core cavity core, wherein at least one first cavity impingement hole is formed thereby in the formed airfoil body such that cooling flow can flow from the first core cavity through the at least one first cavity impingement hole and impinge upon the first exterior wall of the formed airfoil body;
• at least one film exit core attached to the second core cavity core to form 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 in the formed airfoil body;
• and
• a forward central channel formed in the second core cavity core, the forward central channel extending into the second core cavity core to form a forward central ridge that extends from the chevron shape of the first cavity wall into the formed second core cavity, wherein the forward central ridge at least partially divides the formed second core cavity into a two-vortex chamber.