Patent ID: 7669421
Filing Date: 2010-03-02
Classification: F23C,F23R,Y02E,Y02T

Abstract:
1. A combustor of a gas turbine, which is composed of an inner tube and a transition pipe connected together, comprising: an internal swirler composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring; and an external swirler composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring, the internal swirler and the external swirler being disposed within the inner tube, inward swirler vane injection holes disposed in vane surfaces of the inward swirler vanes; outward swirler vane injection holes disposed in vane surfaces of the outward swirler vanes, and fuel supply lines that supply a fuel to the inward and outward swirler injection holes wherein the inward swirler injection holes inject the fuel toward air passing between the inward swirler ring and the outward swirler ring to form an air-fuel mixture in a fuel-rich state, and the outward swirler injection holes inject the fuel toward air passing between the outward swirler ring and the inner tube to form an air-fuel mixture in a fuel-lean state.