FUEL AIR PREMIXER FOR GAS TURBINE ENGINE

摘要

A fuel-air premixer for a combustor of a turbine engine includes a central passage along an axis. The central passage is operable to communicate an unswirled airflow. An outer annular passage is located around the axis and includes a multiple of first swirl vanes that are operable to communicate a first swirled airflow in a first direction. An inner annular passage is located around the axis between the central passage and the outer annular passage. The inner annular passage includes a multiple of second swirl vanes that are operable to communicate a second swirled airflow in a second direction different than the first direction.