Cavity swirl fuel injector for an augmentor section of a gas turbine engine

Abstract

A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

What is claimed is: 
     
         1 . A method of injecting fuel, comprising:
 directing a fuel jet along an axis;   directing first airflow vortices to impinge an edge of the fuel jet and rotate counterclockwise; and   directing second airflow vortices to impinge an edge of the fuel jet and rotate clockwise.   
     
     
         2 . The method of  claim 1 , further comprising directing the fuel jet through an augmentor vane transverse to an exhaust gas flow. 
     
     
         3 . The method of  claim 1 , further comprising directing the first airflow vortices and the second airflow vortices downstream with respect to an exhaust gas flow. 
     
     
         4 . The method of  claim 1 , wherein a gas turbine engine comprises:
 a tubular case;   a center body within the tubular case;   a vane extending radially through a gas path of the gas turbine engine from the tubular case to the center body;   a spraybar mounted within the vane; and   a fuel injector mounted to the spraybar to communicate through the augmentor vane, and wherein the fuel injector is configured to direct the jet of fuel, the first airflow vortices and the second airflow vortices.   
     
     
         5 . The method of  claim 4 , wherein
 the fuel injector comprises a first wall and a bottom wall transverse and perpendicular to the first wall;   the first wall and the bottom wall at least partially form a fuel injector cavity;   a first airflow passage and a second airflow passage extend through said first wall; and   a fuel injection aperture extends through said bottom wall.   
     
     
         6 . The method of  claim 5 , wherein the vane is an augmentor vane arranged in an augmentor section of the gas turbine engine. 
     
     
         7 . The method of  claim 5 , wherein
 the fuel injection aperture is configured to inject the fuel jet; and   said first airflow passage and said second airflow passage are transverse to said fuel jet and are configured to respectively direct the first airflow vortices and the second airflow vortices.   
     
     
         8 . The method of  claim 7 , wherein said first airflow passage and said second airflow passage are arranged upstream of said fuel injection aperture with respect to the exhaust gas path. 
     
     
         9 . The method of  claim 5 , wherein said fuel injector is arranged at about ninety degrees with respect to the exhaust gas path.