Patent ID: 6122916
Filing Date: 2000-09-26
Classification: F23D,F23R

Abstract:
A gas turbine combustor, comprising:a nozzle housing having a nozzle housing base, a main combustion zone located adjacent to said nozzle housing;a diffusion fuel pilot nozzle having a pilot fuel injection port, disposed on the axial centerline of said gas turbine combustor upstream of the main combustion zone, said pilot nozzle extending through said nozzle housing and attached to the nozzle housing base;at least one main nozzle parallel to said pilot nozzle, said main nozzle extending through said nozzle housing and attached to the nozzle housing base; anda fluted pilot cone projecting from the vicinity of the pilot fuel injection port of said pilot nozzle, said fluted pilot cone having an undulated diverged end adjacent to the main combustion zone, said fluted pilot cone forming a pilot flame zone adjacent to the pilot fuel injection port and the undulated diverged end.