Patent ID: 6016658
Filing Date: 2000-01-25
Classification: F23R

Abstract:
A fuel injector for a gas turbine engine combustor, comprising:an elongated straight cylindrical constant diameter injector tube having an outer end and a discharge end and having an elongation axis;a fuel inlet tube;a generally cylindrical coupler having a central bore therethrough, the outer end of said elongated straight cylindrical constant diameter injector tube mounted over one end of said generally cylindrical coupler and, said fuel inlet tube extending through the central bore of said generally cylindrical coupler from the other end of said generally cylindrical coupler and into said elongated straight cylindrical constant diameter injector tube,said elongated straight cylindrical constant diameter injector tube having a plurality of openings therein intermediate said generally cylindrical coupler and said discharge end thereof for the entry of compressed air to mix with fuel from said fuel inlet tube in said elongated straight cylindrical constant diameter injector tube for discharge in a first direction into said gas turbine engine combustor, said elongated straight cylindrical constant diameter injector tube being mounted generally tangentially to an outer wall of said gas turbine engine combustor; anda passage means around said elongated straight cylindrical constant diameter injector tube for flowing compressed air generally radially outward along said elongated straight cylindrical constant diameter injector tube in a second direction, the compressed air to change directions from said second direction to said first direction upon entry into said elongated straight cylindrical constant diameter injector tube through said plurality of openings.