Injector for introducing a fuel-air mixture into a combustion chamber

Abstract

An injector ( 8 ) for introducing a fuel-air mixture into a combustion chamber: has a longitudinal axis ( 44 ) and includes a number of annular curved flow passages. Each flow passage comprises a fuel inlet opening ( 43 ), air inlet openings ( 42 ) and a fuel-air mixture outlet opening ( 9 ). The fuel inlet opening ( 43 ) is connected to a fuel distributor ( 41 ) and has a central axis ( 55 ) which runs perpendicular or parallel to the longitudinal axis ( 44 ) of the injector ( 8 ). The fuel-air mixture outlet opening ( 9 ) has a central axis which runs perpendicular to the longitudinal axis ( 44 ) of the injector ( 8 ). The air inlet openings ( 42 ) each have a central axis ( 54 ) which runs parallel to the longitudinal axis ( 44 ) of the injector ( 8 ).

1 . An injector for introducing a fuel-air mixture into a combustion chamber, the injector comprising:
 a longitudinal axis of the injector;   a plurality of curved flow passages, each flow passage comprising a fuel inlet opening, a plurality of air inlet openings and a fuel-air mixture outlet opening;   a fuel distributor to which the fuel inlet opening is connected;   each fuel-air mixture outlet opening of each curved flow passage has a central axis which runs perpendicular to the longitudinal axis of the injector; and   each air inlet opening of each curved flow passage has a central axis which runs parallel to the longitudinal axis of the injector.   
     
     
         2 . In combustion the injector as claimed in  claim 1 , and a combustion chamber with a combustion chamber wall wherein the injector is arranged on the combustion chamber wall such that the longitudinal axis of the injector runs substantially parallel to or coincides with;
 a longitudinal axis of the combustion chamber.   
     
     
         3 . The injector as claimed in  claim 1 , further comprising the air inlet openings of at least one of the flow passage are arranged in at least one row. 
     
     
         4 . The injector as claimed in  claim 1 , wherein the fuel distributor is of annular design. 
     
     
         5 . The injector ( 8 ) as claimed in  claim 4 , wherein with respect to the longitudinal axis of the injector, the fuel distributor is arranged radially outside the curved flow passages or is arranged, in next to the curved flow passages the axial direction. 
     
     
         6 . The injector as claimed in  claim 1 , wherein the curved flow passages have an angle of curvature that is greater than 0° and less than 180°. 
     
     
         7 . The injector as claimed in  claim 1 , wherein at least one of the curved flow passages has an axis of curvature which runs parallel to the longitudinal axis of the injector. 
     
     
         8 . The injector as claimed in  claim 1 , wherein the injector comprises two disks which are arranged substantially parallel to one another, in the combustion chamber and the disks comprise sidewalls of the flow passages and the air inlet openings. 
     
     
         9 . A combustion chamber which comprises at least one of the injectors as claimed in  claim 1 . 
     
     
         10 . The combustion chamber as claimed in  claim 9 , wherein the combustion chamber further comprises a longitudinal axis, a combustion chamber head end, and a combustion chamber outlet, a combustion chamber wall which extends from the combustion chamber head end to the combustion chamber outlet, a primary zone in the combustion chamber and a secondary zone, which is arranged in the combustion chamber downstream of the primary zone in a main flow direction of the hot gas, and the at least one injector is arranged on the combustion chamber wall at a location and are configured such that the fuel-air mixture outlet openings open into the secondary zone. 
     
     
         11 . The combustion chamber as claimed in  claim 9 , wherein the fuel-air mixture outlet openings are arranged along a circumferential line on the combustion chamber wall. 
     
     
         12 . The combustion chamber as claimed in  claim 9 , further comprising the combustion chamber comprises a liner region which comprises the at least one injector. 
     
     
         13 . The combustion chamber as claimed in  claim 12 , wherein the liner region has a longitudinal axis which coincides with the longitudinal axis of the injector. 
     
     
         14 . The combustion chamber as claimed in  claim 12 , wherein the liner region is a discrete component of the chamber wall. 
     
     
         15 . The combustion chamber as claimed in  claim 9 , wherein the combustion chamber is an annular combustion chamber or as a tubular combustion chamber. 
     
     
         16 . A gas turbine which comprises a combustion chamber as claimed in  claim 10 .