| 摘要 |
<p>The invention refers to a premix burner (10) for a gas turbine, in the form of a double-cone burner, which 5 comprises two partial cone shells (11, 12) which are arranged in a manner in which they are nested one inside the other, forming air inlet ducts (18, 19) between them, through which combustion air (20) from the outside flows into a conical inner space (30) of 10 the premix burner (10), wherein linear rows of holes of injection openings (21), which extend transversely to the flow direction of the combustion air (20), are arranged on the outer walls of the air inlet ducts (18, 19) and through which a gaseous fuel (22) is injected 15 into the combustion air (20) which flows past transversely to them. An improvement in the mixing-through of fuel and combustion air and a reduction of pollutant emissions 20 is achieved by the injection openings (21) having in each case a diameter ratio of diameter of the injection opening to effective outlet diameter of the premix burner which lies between 0.011 and 0.015. 25 The invention additionally refers to a method for reworking such premix burners. (Fig. 1) -- 1N~. I7~ (N - - 'I I -. = (N 1* I 00 _ ~~fJ 4'/4 -(N iJ~ (N</p> |
