Patent ID: 6634175
Filing Date: 2003-10-21
Classification: F23R

Abstract:
A gas turbine combustor comprising:a cylinder circumferentially supported by a plurality of struts fixed at one end to a combustor housing portion of a turbine casing, said cylinder having a center; a pilot nozzle at the center of said cylinder; a plurality of main nozzles around said pilot nozzle; a flow ring having a ring shape and a semicircular cross sectional shape and disposed so as to cover an upstream end of said cylinder which is upstream with respect to a direction of flow inside said cylinder and in said pilot nozzle and said main nozzles while maintaining a predetermined gap with said upstream end; and a porous plate downstream of said flow ring in a space formed between said pilot nozzle and said main nozzles; wherein said semicircular cross sectional shape of said flow ring further comprises two ends of a semicircle defining said semicircular cross sectional shape being extended so as to form an extended semicircular cross sectional shape having a side face, and wherein said porous plate is fixed at a circumference thereof to said side face.