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

A system, comprising:

• a gas turbine engine having a turbine section having circumferentially spaced airfoils, wherein at least one component of the turbine section comprises:
• a fuel injection port formed into a wall of the at least one component, wherein the fuel injection port is configured to direct fuel between successive circumferentially spaced airfoils of the turbine section;
• and
• an inert gas injection port formed into the wall directly upstream of the fuel port, wherein the inert gas port is configured to direct inert gas to flow at least partially around the fuel into a buffer region downstream from the fuel port;
• wherein the fuel port and the inert gas port are arranged along a common axis in a flow direction of the inert gas.

A method, comprising:

• injecting a fuel into a turbine section of a gas turbine engine from a fuel port formed into a wall of at least one component of the turbine section;
• injecting an inert gas toward the injected fuel from an inert gas port formed into the wall directly upstream of the fuel port;
• and
• causing the injected inert gas to occupy at least a portion of a buffer region downstream of the fuel port;
• wherein the fuel port and the inert gas port are arranged along a common axis in a flow direction of the inert gas.