Patent ID: 6301900
Filing Date: 2001-10-16
Classification: F23D,F23R

Abstract:
A combustor for a gas turbine comprising:a nozzle body having one or more nozzle holes at the center of a downstream end wall thereof, said one or more nozzle holes being adapted to eject fuel;a plurality of swirlers located in a space between an outer tubular body disposed around said nozzle body and said nozzle body; anda nozzle cap having a surface of a generally conical shape diverging downstream from said one or more nozzle holes of said nozzle body, said nozzle cap further having an upstream end surface which extends in parallel with said downstream end wall of said nozzle body so as to define a gap therebetween forming a cooling air path,wherein fuel ejected from said one or more nozzle holes is mixed with swirling air blowing from a swirl path formed by said plurality of swirlers, and wherein said surface of a generally conical shape forms a fuel-jet guide for smoothly guiding the fuel ejected from said one or more nozzle holes into the swirl path, and wherein said surface of a conical shape further defines an inlet opening of said fuel-jet guide such that cooling air introduced into said cooling air path flows out along the fuel-jet guide thereby cooling said fuel-jet guide.