Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions

A fuel-air wiser for use in a combustion chamber of a gas turbine engine, the fuel-air mixer comprising:

• an annular fuel injector having a fuel delivery line fluidly connected to an annular fuel distribution manifold, wherein the annular fuel distribution manifold is fluidly connected to a plurality of discrete plain jet orifices and a first radial swirler wherein the first swirler is located upstream from the discrete plain jet orifices and wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler;
• and
• a secondary swirler assembly comprising a second radial swirler wherein the second swirler is located downstream from the discrete plain jet orifices, a swirler exit throat downstream of to second swirler and a swirler exit quarl downstream of the swirler exit throat.

A combustor comprising a fuel-air mixer, the fuel-air mixer comprising:

• an annular fuel injector having a fuel delivery line fluidly connected to an annular fuel distribution manifold, wherein the annular fuel distribution manifold is fluidly connected to a plurality of discrete plain jet orifices and a first radial swirler wherein the first swirler is located upstream from the discrete plain jet orifices and wherein the fuel delivery line is located between swirler airflow passages of the first radial swirler and
• a secondary swirler assembly comprising a second radial swirler wherein the second swirler is located downstream from the discrete plain jet orifices, a swirler exit throat downstream of the second swirler and a swirler exit quarl downstream of the swirler exit throat.