Patent ID: 9500368
Filing Date: 2016-11-22
CPC Classification: F23R

Claim Text:
1. A can annular gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising: a combustor central axis, a plurality of main swirlers with respective swirler axes disposed about, equidistant from, and parallel to the combustor central axis, each main swirler configured to deliver an air fuel mixture flowing therethrough about the respective swirler axis, wherein airfoils of a first of two adjacent swirlers are concentric with and angled in a first direction about a first swirler axis and airfoils of a second swirler axis such that during operation tangential components of flow direction of meeting portions of adjacent air fuel mixtures travel in the same direction; fuel injectors for distributing fuel within each main swirler air fuel mixture in a concentration other than a center rich concentration; and a central pilot swirler disposed on the central axis and delivering a pilot air fuel mixture flowing therethrough.