Burner of a gas turbine having a special lance configuration

摘要

The burner (1) of a gas turbine comprises a tubular body (2) with an inlet (3) for the entrance of an air flow (A), downstream of the inlet (3) vortex generators (4) and a lance (7) projecting into the tubular body (2) and having a terminal portion (10) extending along the longitudinal axis (5) of the burner (1) which is provided with nozzle groups (12) for injecting fuel into the tubular body (2). The nozzle groups (12) lay in an injection plane (15) perpendicular to the axis of the terminal portion (10) of the lance (7). Downstream of the lance (7), the burner (1) has an outlet (11). The ratio x/L between the axial distance x between the side trailing edge of the vortex generator (4) and the injection plane (15), and the length L of the tubular body (2) is less than 0.1052.