US Patent 12007117 Fuel-air mixer for turbine engine combustion section

An apparatus is provided for a turbine engine. This apparatus includes a fuel-air mixer. The fuel-air mixer includes an inner passage, a sidewall, a fuel nozzle, an air swirler and a first quench aperture. The inner passage extends axially along an axis within the fuel-air mixer. The sidewall extends circumferentially around and axially along the inner passage. The fuel nozzle is configured to direct fuel into the inner passage. The air swirler is configured to direct swirled air into the inner passage for mixing with the fuel. The first quench aperture is configured to direct quench air into the inner passage to quench combustion products generated by combusting a mixture of the fuel and the swirled air within the inner passage.