Patent ID: 8943833
Filing Date: 2015-02-03
Classification: F23R

Abstract:
1. A combustor system for a gas turbine engine comprising: a combustor defining a combustor chamber; a fuel air mixer including a chamber disposed along an axis including a bulkhead at a forward end and an opening at an aft end; a first annular passage disposed about the chamber, the first annular passage including a first plurality of vanes to generate a swirled first airflow and a first open end at the aft end of the chamber; a second annular passage disposed about the first annular passage, the second annular passage including a second plurality of vanes to generate a swirled fuel flow and a second open end at the aft end of the chamber; a third annular passage disposed about the second annular passage, the third annular passage including a third plurality of vanes to generate a swirled second airflow and a third open end at the aft end of the chamber; a plurality of openings through the bulkhead of the chamber for communicating a central airflow to the chamber, wherein each of the openings are open to the chamber; and a plurality of fuel tubes disposed about the axis and extending through the bulkhead into the chamber to communicate a second fuel flow to the chamber, wherein the plurality of openings are disposed between the plurality of fuel tubes.