| 摘要 |
PROBLEM TO BE SOLVED: To provide an apparatus and a method for a gas turbine nozzle. SOLUTION: The nozzle (12) includes an inlet (34), an outlet (36), and an axial centerline (44). A shroud (42) surrounding the axial centerline (44) extends from the inlet (34) to the outlet (36) and defines a circumference. The circumference proximate the inlet (34) is greater than the circumference at a first point downstream of the inlet (34), and the circumference at the first point downstream of the inlet (34) is less than the circumference at a second point downstream of the first point. In a method for supplying fuel through the nozzle (12), a first airflow is guided along a first path, and a second airflow is guided along a second path separated from the first path. The method further includes a step of injecting fuel into at least one of the first path or the second path, and a step of accelerating at least one of the first airflow or the second airflow. COPYRIGHT: (C)2011,JPO&INPIT
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