| 摘要 |
A PREMIX BURNER, FOR EXAMPLE FOR A GAS TURBINE, HAVING A CONICAL SWIRL GENERATOR (1) AND A CYLINDRICAL MIXING SECTION (2) WHICH FOLLOWS IT IN THE DIRECTION OF FLOW, INCLUDES A HIGH-PRESSURE ATOMIZER NOZZLE (10) WITH ONE OR MORE FUEL FEED PASSAGES. THE HIGH-PRESSURE ATOMIZER NOZZLE (10) INCLUDES AT LEAST TWO OUTLET PASSAGES, THROUGH WHICH LIQUID FUEL ENTERS THE SWIRL GENERATOR (1), THESE PASSAGES BEING ARRANGED OFF-CENTER WITH RESPECT TO THE LONGITUDINAL AXIS OF THE NOZZLE AND BEING CONFIGURED IN SUCH A WAY THAT THE SPRAY CONE (11) OF THE FUEL IS ORIENTED AT AN ANGLE () WITH RESPECT TO THE LONGITUDINAL AXIS OF THE SWIRL GENERATOR (1) WHICH IS SMALLER THAN THE CONE HALF-ANGLE (α) OF THE SWIRL GENERATOR (1). THE OUTLET PASSAGES IN PARTICULAR HAVE AN INTERNAL GEOMETRY WITH A CONICALLY NARROWED SECTION.
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