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 located 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 located between the second core cavity core and the first core cavity 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;
• 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 a 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 to form a first high momentum jet of impingement air thereon;
• and
• a central channel formed in the second core cavity core extending into the second core cavity core to form a central ridge on 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.

A gas turbine engine comprising:

• an airfoil having 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 includes 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 a first impingement flow flows from the first core cavity through the at least one first cavity impingement hole and impinges upon the first exterior wall to form a first high momentum jet of impingement air thereon;
• and
• a central ridge extending into the second core cavity from at least one of the first cavity wall and the second wall, wherein the central ridge at least partially divides the second core cavity into a two-vortex chamber.