Multi-tube pilot injection into capture vortices in gas turbine engines

A combustor (100) of a gas turbine engine is provided with a first injector (102) and a second injector (104). The first injector surrounds the combustion liner (108) and is positioned at a downstream end of the flow sleeve (106). A dome plate (130) is positioned to receive a fuel/air mixture from the first injector and turn it 180 degrees into a combustion zone formed within the combustion liner. The second injector (104) is positioned radially inward of the combustion liner (108) at an inlet end of the combustion zone and receives only compressed air from the first injector (102). The second injector includes a plurality of air/fuel mixing tubes (122) divided into a radially outer subset of the air/fuel mixing tubes and a radially inner subset of the air/fuel mixing tubes, a first fuel manifold (130) in fluid communication with the radially outer subset of the air/fuel mixing tubes, and a second fuel manifold (132) is in fluid communication with a radially inner subset of the air/fuel mixing tube (122). 一种燃