Carbureted fuel injection system for a gas turbine engine

1. A method of injecting fuel within a gas turbine engine, comprising:

at least partially premixing and prevaporizing fuel from a fuel nozzle with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine, wherein said fuel nozzle is directed substantially transverse with respect to the secondary airflow through said air channel, wherein said vane is located within an augmentor section of the gas turbine engine that is downstream of a combustor section of the gas turbine engine, wherein said secondary airflow is received from a secondary airflow path, and wherein said secondary airflow path is defined by an outer engine structure and an inner engine structure of the gas turbine engine.

2. The method as recited in claim 1 , further comprising:

selectively activating the at least partial premixing and prevaporizing.

3. The method as recited in claim 2 , wherein the selectively activating occurs during a high power operating condition.

4. A fuel injection system for a gas turbine engine comprising:

a vane within an augmentor section of the gas turbine engine that is downstream of a combustor section of the gas turbine engine, the vane in an airflow path within the gas turbine engine, said vane includes an air channel with an outlet in communication with the airflow path; and

a fuel nozzle within said vane operable to inject fuel into said air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within said vane in said air channel prior to entry into the airflow path through the outlet,

wherein said fuel nozzle is directed substantially transverse with respect to the secondary airflow through said air channel,

wherein said secondary airflow is received from a secondary airflow path, and

wherein said secondary airflow path is defined by an outer engine structure and an inner engine structure of the gas turbine engine.

5. The system as recited in claim 4 , wherein the airflow path is a core airflow path within the gas turbine engine.

6. The system as recited in claim 4 , wherein the airflow path is a primary combustion gas exhaust airflow path.

7. The system as recited in claim 4 , further comprising a second fuel injector within said vane, said second fuel injector is positioned downstream with respect to said outlet from said air channel.

8. The system as recited in claim 7 , wherein the airflow path is a primary combustion gas exhaust airflow path, and wherein said second fuel injector directly injects fuel into the primary combustion gas exhaust airflow path.

9. The system as recited in claim 4 , wherein an interior of said vane receives said secondary airflow such that said interior is at a higher pressure than an airflow within the airflow path.

10. A gas turbine engine comprising:

a vane within an augmentor section of the gas turbine engine that is downstream of a combustor section of the gas turbine engine, the vane in an airflow path within the gas turbine engine, said vane includes an air channel with an outlet in communication with the airflow path;

an outer engine structure and an inner engine structure that define a secondary airflow path;

a first fuel nozzle within said vane operable to inject fuel into said air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within said vane in said air channel prior to entry into the airflow path through the outlet; and

a second fuel nozzle within said vane operable to directly inject fuel into the airflow path,

wherein said first fuel nozzle is directed substantially transverse with respect to the secondary airflow through said air channel, and

wherein said secondary airflow is received from the secondary airflow path.

11. The gas turbine engine as recited in claim 10 , further comprising a spraybar within said vane, said spraybar in communication with said first fuel nozzle and said second fuel nozzle.

12. The gas turbine engine as recited in claim 10 , wherein an interior of said vane receives said secondary airflow such that said interior is at a higher pressure than a primary combustion gas exhaust airflow of the airflow path.

13. The gas turbine engine as recited in claim 10 , wherein said airflow path is a core airflow path within the gas turbine engine.

14. The gas turbine engine as recited in claim 10 , wherein the airflow path is a primary combustion gas exhaust airflow path.