16 B09/181-0 The burner of a gas turbine comprises two or more part cone shells (2) arranged offset with respect to one another and defining a cone shaped chamber (1) with longitudinal 5 tangential slots (4) for feeding air (3) therein. A lance (8) carrying a liquid fuel nozzle (12) arranged centrally in the cone shaped chamber (1) is also provided. A portion (14) of the nozzle (12) facing the cone shaped chamber (1) is divergent in shape. A diffuser angle (a) between the 10 wall of the nozzle and a longitudinal axis of the cone shaped chamber (1) is less than 5*. A diverging portion of the nozzle has a diffuser length (L) to nozzle diameter (D) ratio comprised between 2-6. The nozzle diameter (D) is the smaller diameter of the diverging portion (14). 15 (Fig 2) 2/4 B09/181-0 --------------- Fig. 3 17 15, 4 Fig. 4
