System and method for fuel injection in turbine section of gas turbine engine

A system, comprising:

• a turbine section including circumferentially spaced airfoils;
• at least one component of the turbine section comprising:
• an inert gas port formed into a wall of the at least one component, wherein the inert gas port is configured to direct an inert gas between successive circumferentially spaced airfoils of the turbine section in a downstream direction;
• a fuel port formed into the wall upstream of the inert gas port, wherein the fuel port is configured to inject a fuel between the successive circumferentially spaced airfoils in the downstream direction toward the inert gas;
• and
• a hump protruding from a surface of the wall, wherein an opening of the inert gas port is disposed downstream of a crest of the hump, and an opening of the fuel port is disposed upstream of the crest.

A method, comprising:

• injecting an inert gas from an inert gas port formed into a wall of at least one component of a turbine section;
• injecting a fuel in a downstream direction toward the injected inert gas from a fuel port formed into the wall, wherein an opening of the inert gas port is disposed downstream of a crest of a hump protruding from a surface of the wall, and an opening of the fuel port is disposed upstream of the crest;
• and
• causing the injected inert gas to occupy at least a portion of a region downstream of the fuel port and adjacent to the wall.